Entries |
Document | Title | Date |
20080209909 | Gas turbine combustor and fuel supply method for same - A gas turbine combustor includes a liquid fuel nozzle for jetting out liquid fuel, a pre-mixture chamber wall provided with the liquid fuel nozzle at a center thereof, having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out and defining a pre-mixture chamber therein; a plurality of air inlet holes bored through the pre-mixture chamber wall and introducing the combustion air to the pre-mixture chamber such that angles at which the combustion air is introduced to the pre-mixture chamber through the air inlet holes are deflected at least toward the circumferential direction of the pre-mixture chamber wall; and a plurality of gaseous fuel nozzles disposed around the pre-mixture chamber wall in an opposing relation respectively to the plurality of air inlet holes and jetting out gaseous fuel substantially coaxially with axes of the air inlet holes. | 09-04-2008 |
20080216482 | BURNER LANCE - A lance for introducing fuel into a combustion chamber of a burner, in particular of a turbine plant is provided. The lance includes a lance head, a fuel feed, an oxidator feed and a control device. The lance head projects into the combustion chamber and includes a fuel nozzle and an oxidator outlet orifice. The fuel feed extends in the lance and is connected to the fuel nozzle. The oxidator feed extends in the lance head and is connected to the oxidator outlet orifice. The control device controls a flow cross sectional area of the oxidator feed. The control device has a control piston installed in the lance head with stroke adjustability for stroke-dependent controlling of the flow cross sectional area of the oxidator feed. | 09-11-2008 |
20080245074 | Combustor of a gas turbine engine - The present combustor of gas turbine engine includes: a fuel injection unit including a fuel spray part to spray a fuel so that a diffusion combustion region is formed in a combustion chamber, and a pre-mixture supply part to supply a pre-mixture of a fuel and an air so that a pre-mixture combustion region is formed in the combustion chamber; and a fuel supply unit to supply the fuel to the fuel spray part and pre-mixture supply part. The fuel supply unit includes: a pilot fuel passage and a main fuel passage to supply the fuel to the fuel spray part and the pre-mixture supply part, respectively; an assembled fuel passage to supply the fuel to the pilot and main fuel passages; and a fuel distributor disposed at a branch point where the assembled fuel passage is connected to both the pilot and main fuel passages. The fuel distributor is configured to automatically control amounts of the fuel to be distributed to the pilot fuel passage and to the main fuel passage in accordance with the fuel pressure. | 10-09-2008 |
20080289340 | Combustor of a gas turbine engine - The present invention provides a combustor of a gas turbine engine, including: a fuel spray portion configured to spray a fuel so as to create a diffusion combustion region in a combustion chamber; a pre-mixture supply portion configured to supply a pre-mixture gas including the fuel and an air so as to create a pre-mixture combustion region in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion so as to surround the fuel spray portion; and an annular separation portion disposed between a downstream end of the fuel spray portion and a downstream end of the pre-mixture supply portion so as to separate the diffusion combustion region and the pre-mixture combustion region from each other. | 11-27-2008 |
20080302105 | Combustor of a gas turbine engine - The present invention provides a combustor of a gas turbine engine, including: a fuel spray portion configured to spray a fuel so as to create a diffusion combustion region in a combustion chamber, the fuel spray portion including a fuel atomizing portion configured to atomize the fuel, and a diffusion passage portion disposed downstream of the fuel atomizing portion, the diffusion passage portion having a spreading trumpet-like shape and being configured to diffuse the fuel and the air; a pre-mixture supply portion configured to supply a pre-mixture gas including the fuel and an air so as to create a pre-mixture combustion region in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion so as to surround the fuel spray portion; and fuel diffusion restraining member disposed on an inner circumferential face of the diffusion passage portion for restraining a diffusion of an injected fuel by separating a stream of the injected fuel away from the inner circumferential face. | 12-11-2008 |
20090031728 | COMBUSTOR AND A FUEL SUPPLY METHOD FOR THE COMBUSTOR - A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The air hole plate includes a plurality of rows disposed concentrically of a plurality of air holes jetting coaxial jets of fuel and air into the chamber. A first fuel nozzle and a second fuel nozzle are disposed near a fuel hole for jetting fuel into an air hole row on an inner peripheral side. The first fuel nozzle is structured to suppress turbulence of surrounding air flow and the second fuel nozzle is structured to promote turbulence of a surrounding air flow. | 02-05-2009 |
20090044537 | APPARATUS AND METHOD FOR EXTERNALLY LOADED LIQUID FUEL INJECTION FOR LEAN PREVAPORIZED PREMIXED AND DRY LOW NOX COMBUSTOR - A fuel injector stick for a gas turbine includes: a body of a length, L, the body including an annular shape forming a fuel channel and adapted for insertion into a premixer of the gas turbine; a mounting section for mounting the injector stick to the gas turbine; and a nozzle for injecting fuel into the premixer of the gas turbine. A gas turbine combustor and a method for changing fuel injector sticks are provided. | 02-19-2009 |
20090056334 | SYSTEM AND METHOD FOR FUEL AND AIR MIXING IN A GAS TURBINE - A gas turbine system including a source of gas coupled to a source of fuel wherein the gas and the fuel are combined to form a mixture of gas and fuel prior to the mixture being introduced to a fuel nozzle of the gas turbine system. | 03-05-2009 |
20090056335 | Gas turbine engine combustor assembly having integrated control valves - A combustor assembly for a gas turbine engine includes a combustor endcover having at least one fuel circuit and mounted thereto a plurality of pre-mixers and at least one control valve. The at least one control valve is fluidly connected to the at least one fuel circuit and operatively connected to a controller. The controller selectively operates the at least one control valve to deliver fuel through the at least one fuel circuit to the plurality of pre-mixers in order to achieve an enhanced level of operational flexibility by providing individual combustion chamber control. | 03-05-2009 |
20090056336 | Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine - A burner for use in a combustion system of an industrial gas turbine. The burner includes a fuel/air premixer including a splitter vane defining a first, radially inner passage and a second, radially outer passage, the first and second passages each having air flow turning vane portions which impart swirl to the combustion air passing through the premixer. The vane portions in each passage are commonly configured to impart a same swirl direction in each passage. A plurality of splitter vanes may be provided to define three or more annular passages in the premixer. | 03-05-2009 |
20090071157 | MULTI-STAGE AXIAL COMBUSTION SYSTEM - A gas turbine combustion system is provided comprising a combustion chamber ( | 03-19-2009 |
20090071158 | FUEL INJECTOR FOR INJECTING FUEL INTO A TURBOMACHINE COMBUSTION CHAMBER - A fuel injector for injecting fuel into a turbomachine combustion chamber, the injector presenting an injector nose for connection to an injection system fastened to the end wall of said combustion chamber, the injector nose comprising:
| 03-19-2009 |
20090077972 | TOROIDAL RING MANIFOLD FOR SECONDARY FUEL NOZZLE OF A DLN GAS TURBINE - A toroidal ring manifold for effectively dispersing premixing fuel with air in the secondary fuel nozzle of a combustor for a Dry Low NO | 03-26-2009 |
20090100837 | Lean premix burner for a gas-turbine engine - A lean premix burner for a gas-turbine engine includes an annular center body ( | 04-23-2009 |
20090113893 | Pilot mixer for mixer assembly of a gas turbine engine combustor having a primary fuel injector and a plurality of secondary fuel injection ports - A mixer assembly for use in a combustion chamber of a gas turbine engine including a pilot mixer, a main mixer, and a fuel manifold. The pilot mixer includes: an annular pilot housing having a hollow interior; a primary fuel injector mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing; a plurality of axial swirlers positioned upstream from the primary fuel injector, each of the plurality of swirlers having a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the primary fuel injector; and, a plurality of secondary fuel injection ports for introducing fuel into the hollow interior of the pilot housing. The main mixer further includes: a main housing surrounding the pilot housing and defining an annular cavity; a plurality of fuel injection ports for introducing fuel into the cavity; and, at least one swirler positioned upstream from the plurality of fuel injection ports, each of the main mixer swirlers having a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the main mixer fuel injection ports. The fuel manifold is in flow communication with the plurality of secondary fuel injection ports in the pilot mixer and the plurality of fuel injection ports in the main mixer. | 05-07-2009 |
20090139236 | PREMIXING DEVICE FOR ENHANCED FLAMEHOLDING AND FLASH BACK RESISTANCE - A premixing device is provided. The premixing device includes a fuel inlet configured to introduce a fuel within the premixing device and an air inlet configured to introduce air within the premixing device. The premixing device also includes a plurality of swirler vanes configured to provide a swirl movement to the fuel and/or air to facilitate mixing of the fuel and air to form a gaseous pre-mix, wherein a shape of each of the plurality of swirler vanes is selected to control an axial velocity profile of the fuel and/or air within the premixing device. | 06-04-2009 |
20090139237 | Low residence combustor fuel nozzle - Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition. | 06-04-2009 |
20090158742 | METHOD AND APPARATUS FOR MIXING SUBSTANCES - A combustor assembly for a gas powered turbine includes a premix section to mix a first selected volume of fuel with a selected oxidizer. The premix section includes an injector plate that includes a porosity according to selected characteristics, such as pore size, pore density, pore distribution, and other selected characteristics. Therefore, the fuel may be provided through the porous plate to the premix area in a selected uniform flux. | 06-25-2009 |
20090173074 | INTEGRATED FUEL NOZZLE IFC - Disclosed is a fuel nozzle for a gas turbine including a center body defining one or more fuel passages and an inlet flow conditioner. The inlet flow conditioner includes a substantially tubular hub, a substantially tubular outer land, and a plurality of spars extending radially outwardly from the hub to the outer land. The plurality of spars together with the hub and outer land define a plurality of fluid flow passages capable of removing circumferential and radial variation from fluid flow entering the fuel nozzle. The inlet flow conditioner is formed as a single unitary component. Further disclosed is a method of operating the gas turbine including the fuel nozzle. | 07-09-2009 |
20090173075 | BURNER AND GAS TURBINE COMBUSTOR - A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet. | 07-09-2009 |
20090183511 | SWOZZLE DESIGN FOR GAS TURBINE COMBUSTOR - Disclosed is a fuel nozzle for a combustor of a gas turbine engine includes a nozzle inlet, a combustion area and a swirler disposed between the nozzle inlet and combustion area. The swirler includes a plurality of swirler vanes, each swirler vane capable of creating a pressure difference in fluid flow through the swirler between a pressure side and suction side of the swirler vane. The swirler further includes at least one through airflow hole located in at least one swirler vane of the plurality of swirler vanes. The at least one through airflow hole is capable of utilizing the pressure difference between the pressure side and suction side to promote fluid flow through the at least one airflow hole. Also disclosed is a method for operating a combustor. | 07-23-2009 |
20090188255 | COMBUSTOR END CAP ASSEMBLY - A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate. | 07-30-2009 |
20090205339 | AIR-COOLED SWIRLERHEAD - A combustor for a gas turbine engine is disclosed which is able to operate with high combustion efficiency, and low nitrous oxide emissions during gas turbine operations. The combustor consists of a can-type configuration which combusts fuel premixed with air and delivers the hot gases to a turbine. Fuel is premixed with air through a swirler and is delivered to the combustor with a high degree of swirl motion about a central axis. This swirling mixture of reactants is conveyed downstream through a flow path that expands; the mixture reacts, and establishes an upstream central recirculation flow along the central axis. A cooling assembly is located on the swirler co-linear with the central axis in which cooler air is conveyed into the prechamber between the recirculation flow and the swirler surface. | 08-20-2009 |
20090211255 | GAS TURBINE COMBUSTOR FLAME STABILIZER - A gas turbine combustor is presented, which includes a combustion chamber that is positioned downstream of a premixing chamber. The premixing chamber includes at least one opening for ingesting air. At least one primary fuel nozzle is disposed to discharge fuel into the premixing chamber. The fuel discharged from the primary fuel nozzle mixes with the ingested air in the premixing chamber to provide a fuel air mix. A secondary fuel nozzle is disposed proximate the combustion chamber to discharge fuel at the combustion chamber. A stabilizer is disposed at the secondary fuel nozzle so as to be positioned in close proximity to a flame when fuel at the secondary fuel nozzle is ignited. The stabilizer is composed of a material having the ability to absorb heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame. A method of stabilizing a flame in a gas turbine combustor is also presented. The method including discharging fuel at a combustion chamber of the gas turbine combustor and positioning a stabilizer in close proximity to a flame when the fuel at a combustion chamber is ignited. The stabilizer absorbing heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame. | 08-27-2009 |
20090217669 | Fuel nozzles - In order to achieve better fuel distribution despite an oversized fuel injector nozzle relative to the impingement cross-section of an air flow directed towards that nozzle, an asymmetric distribution of fuel is provided. This asymmetric distribution is achieved by providing fuel distribution structures about the injector nozzle which present varying amounts of fuel to the air flow dependent upon the localised flow pressure in the air flow presented to the nozzle. Such asymmetric distribution of fuel is achieved by providing passages or jets of varying cross-section or distribution/spacing at different parts of the fuel injection nozzle dependent upon incident flow pressure. Thus, both parts of the injector nozzle directly impinged by the air flow generally present more fuel to that flow compared to depleted flow pressure zones of the air flow. | 09-03-2009 |
20090241547 | Gas turbine fuel injector for lower heating capacity fuels - A fuel injector for a gas turbine engine includes a stem extending along a longitudinal axis from a proximal end to a distal end. The stem includes one or more fuel tubes configured to deliver a fuel toward the distal end of the stem, and a pilot assembly coupled to the distal end of the stem. The pilot assembly includes one or more components configured to inject fuel into a combustor of the engine. The fuel injector also includes a substantially tubular premix barrel extending along the longitudinal axis from a first end to a second end. The premix barrel is circumferentially disposed about the stem and configured to couple with the combustor at the second end. The fuel injector also includes an annular premix duct formed between the premix barrel and the stem. The premix duct includes an air inlet port at the first end, and a plurality of first orifices located downstream of the air inlet port. The first orifices are configured to inject fuel from the fuel tube into the premix duct. The premix duct also includes a plurality of second orifices located downstream of the first orifices. The second orifices are configured to inject fuel from the fuel tube into the premix duct. | 10-01-2009 |
20090255258 | Pre-filming air-blast fuel injector having a reduced hydraulic spray angle - An air-blast fuel injector is disclosed that includes an on-axis inner air circuit, a fuel circuit radially outboard of the inner air circuit, the fuel circuit having an axially converging pre-filming chamber and an axially diverging pre-filming surface extending from the pre-filming chamber to an exit annulus and an outer air circuit radially outboard of the fuel circuit communicating with the exit annulus of the axially diverging pre-filming surface. | 10-15-2009 |
20090255259 | MIXER FOR A COMBUSTOR - A mixer having a unitary construction is disclosed comprising an annular housing having an axis and at least a first swirler having a plurality of vanes arranged circumferentially around the axis such that circumferentially adjacent vanes form at least one flow passage that is oriented at least partially in an axial direction with respect to the axis. In another exemplary embodiment, a mixer having a unitary construction is disclosed comprising a swirler having a plurality of radial vanes arranged circumferentially around the axis and oriented at least partially in a radial direction. | 10-15-2009 |
20090255260 | VENTURI - A venturi is disclosed, the venturi comprising a mixing cavity surrounded circumferentially by an annular venturi wall, and a swirler having a plurality of vanes arranged circumferentially around a swirler axis, wherein the swirler and the annular venturi wall have a unitary construction. In another exemplary embodiment the venturi comprises an annular venturi wall, a swirler located at an axially forward portion of the venturi, the swirler having a plurality of vanes arranged circumferentially around a swirler axis, and a heat shield located axially aft from the swirler, wherein the annular venturi wall, the swirler and the heat shield have a unitary construction. | 10-15-2009 |
20090255261 | METHOD OF MANUFACTURING A UNITARY VENTURI - A method for fabricating a unitary venturi is disclosed, the method comprising the steps of determining three-dimensional information of the unitary venturi having an annular venturi wall and a swirler having a plurality of vanes arranged circumferentially around a swirler axis, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary venturi, and successively forming each layer of the unitary venturi by fusing a metallic powder using laser energy. Exemplary embodiments are disclosed, showing a unitary venturi comprising an annular venturi wall having a swirler axis and a heat shield located at an end wherein unitary venturi is made by using a rapid manufacturing process. In one aspect of the invention, the rapid manufacturing process is a laser sintering process. | 10-15-2009 |
20090266079 | Premix Nozzles and Gas Turbine Engine Systems Involving Such Nozzles - Premix nozzles and gas turbine engine systems involving such nozzles are provided. In this regard, a representative industrial gas turbine engine includes: a combustion section having a nozzle assembly operative to provide a fuel-air mixture for combustion, the nozzle assembly having an array of shuttered nozzles and non-shuttered nozzles; each of the shuttered nozzles being operative in an open position, in which air is directed through the shuttered nozzle for mixing with fuel, and a closed position, in which a reduced amount of air is directed through the shuttered nozzle; each of the shuttered nozzles being inoperative to independently alter an amount of air being directed therethrough. | 10-29-2009 |
20090272116 | AXIALLY STAGED COMBUSTION SYSTEM FOR A GAS TURBINE ENGINE - An axially staged combustion system is provided for a gas turbine engine comprising a main body structure having a plurality of first and second injectors. First structure provides fuel to at least one of the first injectors. The fuel provided to the one first injector is adapted to mix with air and ignite to produce a flame such that the flame associated with the one first injector defines a flame front having an average length when measured from a reference surface of the main body structure. Each of the second injectors comprising a section extending from the reference surface of the main body structure through the flame front and having a length greater than the average length of the flame front. Second structure provides fuel to at least one of the second injectors. The fuel passes through the one second injector and exits the one second injector at a location axially spaced from the flame front. | 11-05-2009 |
20090277176 | PURE AIR BLAST FUEL INJECTOR - An air blast fuel injector for a gas turbine engine includes an elongate feed arm having an inlet fitting for receiving fuel and for distributing the fuel to first and second fuel delivery conduits extending through the feed arm. A nozzle body is operatively connected to the feed arm. The nozzle body includes an on-axis inner air circuit and fuel circuitry radially outboard of the inner air circuit for delivering fuel to a fuel swirler outboard of the inner air circuit. The fuel circuitry includes a first fuel circuit configured and adapted to deliver fuel to the fuel swirler from the first fuel conduit of the feed arm and a second fuel circuit configured and adapted to deliver fuel to the fuel swirler from the second fuel conduit of the feed arm. | 11-12-2009 |
20090282831 | METHOD FOR REDUCING EMISSIONS FROM A COMBUSTOR - A modification method for reducing emissions from an annular shaped combustor of a gas turbine plant, having uniformly spaced circumferentially mounted premix burners ( | 11-19-2009 |
20090293482 | FUSE FOR FLAME HOLDING ABATEMENT IN PREMIXER OF COMBUSTION CHAMBER OF GAS TURBINE AND ASSOCIATED METHOD - A fuel nozzle assembly for a combustor of a gas turbine including: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front proximate to a combustion section of the combustor; an outer casing around the inner tube, wherein an air passage is defined between the outer casing and the inner tube; a gas conduit arranged in the air passage and having an outlet proximate to the front of the nozzle body, wherein fuel starts flowing through the expandable conduit only after a flashback condition occurs in the combustor, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein the gas conduit has an inlet open to the premix fuel passage. | 12-03-2009 |
20100000218 | GAS TURBINE COMBUSTOR AND FUEL SUPPLY METHOD FOR SAME - A gas turbine combustor for mixing fuel into combustion air introduced from a compressor, burning an air-fuel mixture, and supplying produced combustion gas to a gas turbine. The combustor has a liquid fuel nozzle for jetting out liquid fuel and a pre-mixture chamber wall having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out from the liquid fuel nozzle, and defining a pre-mixture chamber therein. A plurality of gaseous fuel nozzles are disposed around the pre-mixture chamber wall in an opposing relation respectively to a plurality of air inlet holes bored through the pre-mixture chamber wall and jet out gaseous fuel substantially coaxially with the axes of the air inlet holes. | 01-07-2010 |
20100011770 | Gas Turbine Premixer with Cratered Fuel Injection Sites - A premixer for a gas turbine combustor includes a swirler including a plurality of turning vanes that impart swirl velocity to airflow through the premixer, and at least one fuel injection site enabling fuel to mix with the airflow in the premixer. The fuel injection site terminates in a cratered hole. The cratered hole increases mixing efficiency and increases flashback/flameholding resistance. | 01-21-2010 |
20100018208 | TURBINE ENGINE FLOW SLEEVE - A flow sleeve for use in a turbine engine including a compressor section, a combustion section, and a turbine section downstream from the combustion section. The flow sleeve includes a sleeve wall defining a pre-mixing passage of the combustion section and has a forward end proximate to a cover plate of the combustion section and an opposed aft end. The sleeve wall includes a first wall section extending axially from the sleeve wall forward end and a second wall section extending from the first wall section between the forward and aft ends of the sleeve wall toward the aft end of the sleeve wall A cavity is formed between the first wall section and the second wall section. | 01-28-2010 |
20100024426 | Hybrid Fuel Nozzle - A hybrid fuel combustion nozzle for use with natural gas, syngas, or other types of fuels. The hybrid fuel combustion nozzle may include a natural gas system with a number of swozzle vanes and a syngas system with a number of co-annular fuel tubes. | 02-04-2010 |
20100031661 | Lean direct injection diffusion tip and related method - A nozzle for a gas turbine combustor includes a first radially outer tube defining a first passage having an inlet and an outlet, the inlet adapted to supply air to a reaction zone of the combustor. A center body is located within the first radially outer tube, the center body including a second radially intermediate tube for supplying fuel to the reaction zone and a third radially inner tube for supplying air to the reaction zone. The second intermediate tube has a first outlet end closed by a first end wall that is formed with a plurality of substantially parallel, axially-oriented air outlet passages for the additional air in the third radially inner tube, each air outlet passage having a respective plurality of associated fuel outlet passages in the first end wall for the fuel in the second radially intermediate tube. The respective plurality of associated fuel outlet passages have non-parallel center axes that intersect a center axis of the respective air outlet passage to locally mix fuel and air exiting said center body. | 02-11-2010 |
20100037614 | ULTRA LOW INJECTION ANGLE FUEL HOLES IN A COMBUSTOR FUEL NOZZLE - Disclosed is a fuel nozzle for a combustor including a mixing passage through which fluid is directed toward a combustion area and a plurality of swirler vanes disposed in the mixing passage. Each swirler vane of the plurality of swirler vanes includes at least one fuel hole through which fuel enters the mixing passage in an injection direction substantially parallel to an outer surface of the plurality of swirler vanes thereby decreasing a flameholding tendency of the fuel nozzle. Further disclosed is a method of operating a fuel nozzle for a combustor including flowing a fluid through a mixing passage past a plurality of swirler vanes and injecting a fuel into the mixing passage in an injection direction substantially parallel to an outer surface of the plurality of swirler vanes. | 02-18-2010 |
20100043440 | Gas Turbine Burner and Method of Operating a Gas Turbine Burner - The invention is based on a gas turbine burner comprising a combustion zone for burning a mixture consisting of combustion exhaust gas to which fuel gas is added, and comprising a fuel intermixing arrangement having a fuel nozzle for spraying the fuel gas into the combustion exhaust gas. In order to achieve low-pollutant and uniform combustion, it is proposed that the fuel intermixing arrangement be designed for spraying the fuel gas into the combustion exhaust gas at at least 0.2 times the speed of sound. | 02-25-2010 |
20100050642 | MULTI-TUBE ARRANGEMENT FOR COMBUSTOR AND METHOD OF MAKING THE MULTI-TUBE ARRANGEMENT - A fuel injector tube includes a one piece, unitary, polygonal tube having an inlet end and an outlet end. The fuel injector tube further includes a fuel passage extending from the inlet end to the outlet end along a longitudinal axis of the polygonal tube, a plurality of air passages extending from the inlet end to the outlet end and surrounding the fuel passage, and a plurality of fuel holes. Each fuel hole connects an air passage with the fuel passage. The inlet end of the polygonal tube is formed into a fuel tube. A fuel injector includes a plurality of fuel injector tubes and a plate. The plurality of fuel tubes are connected to the plate adjacent the inlet ends of the plurality of fuel injector tubes. | 03-04-2010 |
20100050643 | Gas Turbine Engine Systems and Methods Involving Enhanced Fuel Dispersion - Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased. | 03-04-2010 |
20100050644 | Fuel injector - A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface. | 03-04-2010 |
20100058763 | SEGMENTED ANNULAR COMBUSTOR - A combustor for use in a turbine engine including a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. An inner annulus wall extends from a burner end of the combustor to an outlet end of the combustor. An outer annulus wall is disposed outwardly from the inner annulus wall and extends from the burner end of the combustor to the outlet end of the combustor. A passageway is formed between the inner annulus wall and the outer annulus wall and extends from a combustion zone to the outlet end of the combustor. A plurality of symmetrically distributed section walls extends between the inner annulus wall and the outer annulus wall from the burner end of the combustor toward the outlet end of the combustor. The section walls divide the combustion zone into a plurality of segments. | 03-11-2010 |
20100064691 | FLASHBACK RESISTANT PRE-MIXER ASSEMBLY - A pre-mixer assembly associated with a fuel supply system for mixing of air and fuel upstream from a main combustion zone in a gas turbine engine. The pre-mixer assembly includes a swirler assembly disposed about a fuel injector of the fuel supply system and a pre-mixer transition member. The swirler assembly includes a forward end defining an air inlet and an opposed aft end. The pre-mixer transition member has a forward end affixed to the aft end of the swirler assembly and an opposed aft end defining an outlet of the pre-mixer assembly. The aft end of the pre-mixer transition member is spaced from a base plate such that a gap is formed between the aft end of the pre-mixer transition member and the base plate for permitting a flow of purge air therethrough to increase a velocity of the air/fuel mixture exiting the pre-mixer assembly. | 03-18-2010 |
20100064692 | BURNER FUEL STAGING - The invention relates to a fuel-air premixing arrangement with a plurality of fuel injection openings. The fuel injection openings are grouped into at least two groups and arranged on one circle in alternating order. Each group has a common rail for supplying fuel to the respective group. A valve element is arranged in at least one common rail. | 03-18-2010 |
20100077757 | COMBUSTOR FOR A GAS TURBINE ENGINE - A combustor ( | 04-01-2010 |
20100089065 | FUEL DELIVERY SYSTEM FOR A TURBINE ENGINE - A fuel delivery system for a turbine engine has at least one fuel injector having an upstream orifice arrangement that produces a first pressure drop of flowing fuel and a downstream orifice arrangement that produces a second pressure drop of the flowing fuel. The upstream orifice arrangement or the downstream orifice arrangement includes a noncylindrical orifice. | 04-15-2010 |
20100095675 | Combustor Burner Vanelets - The present application provides a burner for use with a combustor of a gas turbine engine. The burner may include a center hub, a shroud, a pair of fuel vanes extending from the center hub to the shroud, and a vanelet extending from the center hub and/or the shroud and positioned between the pair of fuel vanes. | 04-22-2010 |
20100095676 | Multiple Tube Premixing Device - The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes. | 04-22-2010 |
20100101229 | Flame Holding Tolerant Fuel and Air Premixer for a Gas Turbine Combustor - A fuel nozzle with active cooling is provided. It includes an outer peripheral wall, a nozzle center body concentrically disposed within the outer wall in a fuel and air pre-mixture. The fuel and air pre-mixture includes an air inlet, a fuel inlet and a premixing passage defined between the outer wall in the center body. A gas fuel flow passage is provided. A first cooling passage is included within the center body in a second cooling passage is defined between the center body and the outer wall. | 04-29-2010 |
20100107641 | METHOD AND APPARATUS FOR AFFECTING A RECIRCULATION ZONE IN A CROSS FLOW - Disclosed is a cross flow apparatus including a surface and at least one outlet located at the surface. The cross flow apparatus further includes at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the at least one outlet downstream from the at least one outlet. | 05-06-2010 |
20100107642 | FEED INJECTOR SYSTEM - A feed injector system comprises a movable central member, a first member substantially concentric with the central member to define a first channel for conveying a first fluid oxidizer stream, a second member substantially concentric with the first member to define a second channel for conveying a fuel feed, and a third member substantially concentric with the second member to define a third channel for conveying a second fluid oxidizer steam. The first member and the second member are configured to enhance instability in the fuel feed emanating from the second channel. | 05-06-2010 |
20100115953 | Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method - An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length. | 05-13-2010 |
20100115954 | Gas turbine fuel injector with a rich catalyst - A fuel injector for a gas turbine engine may include a pilot assembly extending along a longitudinal axis. The pilot assembly may be configured to direct a pilot fuel-air mixture to a combustor of the gas turbine engine. The fuel injector may also include a rich catalyst module circumferentially disposed about the pilot assembly. The catalyst module may be configured to simultaneously direct a stream of compressed air and a stream of first fuel-air mixture therethrough without intermixing. The fuel injector may also include a post mix zone disposed downstream of the catalyst module. The post mix zone may be configured to mix the compressed air and the first fuel air mixture to create a main fuel-air mixture. The fuel injector may further include an air swirler disposed downstream of the post mix zone. The air swirler may be configured to direct the main fuel-air mixture to the combustor without intermixing with the pilot fuel-air mixture. | 05-13-2010 |
20100126174 | GAS TURBINE COMBUSTION CHAMBER - A combustion chamber including: a flame tube having, in the direction of flow, a mixing zone for mixing a fuel with air to form a fuel-air mixture, as well as a primary combustion zone and a post-primary combustion zone, at least one opening being provided in the area of the mixing zone and in the area of the post-primary combustion zone in order to conduct compressed air into the flame tube, wherein supplied compressed air is used to cool the flame tube and, via the openings in the area of the mixing zone and in the area of the post-primary combustion zone, passes partly into the mixing zone and into the post-primary combustion zone. | 05-27-2010 |
20100139280 | MULTI-TUBE THERMAL FUSE FOR NOZZLE PROTECTION FROM A FLAME HOLDING OR FLASHBACK EVENT - A protection system for a pre-mixing apparatus for a turbine engine, includes: a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish a fuel delivery plenum; and a plurality of fuel mixing tubes that extend through at least a portion of the fuel delivery plenum, each of the plurality of fuel mixing tubes including at least one fuel feed opening fluidly connected to the fuel delivery plenum; at least one thermal fuse disposed on an exterior surface of at least one tube, the at least one thermal fuse including a material that will melt upon ignition of fuel within the at least one tube and cause a diversion of fuel from the fuel feed opening to at least one bypass opening. A method and a turbine engine in accordance with the protection system are also provided. | 06-10-2010 |
20100139281 | Fuel injector arrangment having porous premixing chamber - A fuel injector arrangement for a turbine engine is disclosed. The fuel injector arrangement may have a combustion chamber, a plenum, an injector, and a premixing chamber configured to receive the injector. The premixing chamber may be at least partially disposed within the plenum and open to the combustion chamber. The premixing chamber may have at least one passageway configured to allow air from the plenum to enter and mix with fuel from the injector to form an air/fuel mixture within the premixing chamber, and a porous annular wall configured to allow air from the plenum to enter and create a lean boundary layer at the porous annular wall. | 06-10-2010 |
20100139282 | Oxidizing Fuel in Multiple Operating Modes - A fuel oxidizer system is operated in a first operating mode. In the first operating mode, a mixture that includes fuel from a fuel source is compressed in a compressor of the fuel oxidizer system; the fuel of the compressed mixture is oxidized in a reaction chamber of the fuel oxidizer system; and the oxidized fuel is expanded to generate rotational kinetic energy. The fuel oxidizer system is operated in a second operating mode. In the second operating mode, fuel from the fuel source is directed to bypass the compressor, and the fuel that bypassed the compressor is oxidized in the reaction chamber. | 06-10-2010 |
20100146979 | FUEL DISTRIBUTOR - A swirler including a fuel distributor is provided. Each fuel distributor includes a distribution element defining a cavity, an inlet opening arranged in the distribution element, at least one outlet opening arranged in the distribution element, and at least one third opening arranged in the distribution element, the cross-section of the at least one third opening being larger than the cross-section of the at least one outlet opening | 06-17-2010 |
20100162710 | Pre-Mix Combustion System for a Gas Turbine and Method of Operating of operating the same - The invention is related to a gas turbine pre-mix combustion system comprising: at least one combustor with a combustor wall partly surrounding a combustion zone; at least one mixing duct including an air passage leading to an outlet opening being open towards the combustion zone; and one or more fuel injection openings leading into the air passage and connecting it to one or more fuel supply passages so as to allow the injection of fuel into air flowing through the air passage. The locations of at least two outlet openings or at least two sections of a single outlet opening and the orientation of downstream sections of the respective air passages or air passage are chosen such that fuel/air mixtures flowing out of the outlet openings or said sections of a single outlet opening show opposed flow paths so as to impinge on each other in the combustion zone. | 07-01-2010 |
20100170250 | Fuel Plenum Vortex Breakers - The present application provides a manifold for use with a gas turbine. The manifold may include a fuel passage and a swozzle vane in communication with the fuel passage. The swozzle vane may include a fuel plenum in communication with one or more fuel holes and a vortex breaker positioned about the fuel holes. | 07-08-2010 |
20100175381 | SWIRLER - A swirler including a plate normal to a central axis of the swirler, a plurality of vane cross-sections arranged on the plate and radially positioned about the central axis and a plurality of twisted vanes is provided. The twisted part of each vane is twisted around the central axis wherein the cross section of the twisting vane is normal to the central axis. In one aspect, each vane has an essentially triangular cross section. | 07-15-2010 |
20100180599 | Insertable Pre-Drilled Swirl Vane for Premixing Fuel Nozzle - A swirl vane is independently connectable to a central hub assembly of a gas turbine. The swirl vane includes a structural body and at least one fuel delivery passage including a corresponding at least one fuel port defined within the structural body. At least one connecting tab is cooperable with the structural body and is connectable to the central hub assembly. | 07-22-2010 |
20100192578 | SYSTEM AND METHOD FOR SUPPRESSING COMBUSTION INSTABILITY IN A TURBOMACHINE - A system for suppressing combustion instability in a turbomachine includes at least one combustion chamber operatively connected to the turbomachine, and at least one pre-mixer mounted to the at least one combustion chamber. The at least one pre-mixer is configured to receive an amount of fuel and an amount of air that is combined and discharged into the at least one combustion chamber. In addition, the turbomachine includes a combustion instability suppression system operatively associated with the at least one pre-mixer. The combustion instability suppression system is configured to create a combustion asymmetry. The combustion asymmetry facilitates combustion instability suppression in the turbomachine. | 08-05-2010 |
20100192579 | Apparatus for Fuel Injection in a Turbine Engine - In one embodiment, a system includes a fuel nozzle that includes a fuel injector configured to output a fuel flow and a premixer tube disposed about the fuel flow output from the fuel injector. The premixer tube includes a perforated portion and a non-perforated portion, and the non-perforated portion is downstream of the perforated portion. | 08-05-2010 |
20100192580 | Combustion System Burner Tube - A combustor includes a burner tube that receives fuel for combustion from a fuel delivery system. An axial swirler is installed in the burner tube. The burner tube is flared downstream of the swirler. The structure provides for improved combustion stability while extending lean blowout and low frequency dynamics margins, which in turn serve to further reduce NOx emissions. | 08-05-2010 |
20100192581 | PREMIXED DIRECT INJECTION NOZZLE - A fuel/air mixing tube for use in a fuel/air mixing tube bundle is provided. The fuel/air mixing tube includes an outer tube wall extending axially along a tube axis between an inlet end and an exit end, the outer tube wall having a thickness extending between an inner tube surface having a inner diameter and an outer tube surface having an outer tube diameter. The tube further includes at least one fuel injection hole having a fuel injection hole diameter extending through the outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back. | 08-05-2010 |
20100192582 | COMBUSTOR NOZZLE - A secondary nozzle is provided for a gas turbine. The secondary nozzle includes a flange and an elongated nozzle body extending from the flange. At least one premix fuel injector is spaced radially from the nozzle body and extends from the flange generally parallel to the nozzle body. At least one second nozzle tube is fluidly connected to the fuel source and spaced radially outward from the first nozzle tube with a proximal end fixed to the flange. The second nozzle tube has a distal end, spaced from the proximal end, with at least one aperture therein. A passageway extends between the proximal end and the distal end of the second nozzle tube, with the passageway fluidly connecting to the fuel source and the aperture. | 08-05-2010 |
20100192583 | Non-rotational stabilization of the flame of a premixing burner - A method for stabilizing the flame of a premixing burner, comprising a reaction chamber containing a fluid is provided. The method includes injecting an air-fuel mixture into the reaction chamber at a speed that is different from that of the fluid present in the reaction chamber, adjusting the speed such that vortices form at the boundary between the air-fuel mixture and the surrounding fluid. A premixing burner including a reaction chamber and at least one premixing spray nozzle opening into the reaction chamber is also provided. The premixing burner injects an air-fuel mixture into the reaction chamber at a speed that is different from that of the surrounding fluid, the speed being adjusted such that vortices from at the boundary between the air-fuel mixture and the surrounding fluid. | 08-05-2010 |
20100199674 | FUEL NOZZLE MANIFOLD - A fuel nozzle manifold comprising a flange, a stem and a swirler is provided. The flange has a first fluid inlet fluidly connected to a radially extending first flow passage, the stem includes at least a first axially extending and only partially circumferentially extending flow channel, and the swirler has at least a first radially extending premix passage. The flange and the stem can comprise a homogeneous component, or two separate components fluidly connecting the first axially extending flow channel to the first flow passage, to form a fluid connection between the flange and the stem, the swirler comprises another component fitted together with the flange and stem component and fluidly connecting the first premix passage and the first flow channel. | 08-12-2010 |
20100218501 | PREMIXED DIRECT INJECTION DISK - A fuel/air mixing disk for use in a fuel/air mixing combustor assembly is provided. The disk includes a first face, a second face, and at least one fuel plenum disposed therebetween. A plurality of fuel/air mixing tubes extend through the pre-mixing disk, each mixing tube including an outer tube wall extending axially along a tube axis and in fluid communication with the at least one fuel plenum. At least a portion of the plurality of fuel/air mixing tubes further includes at least one fuel injection hole have a fuel injection hole diameter extending through said outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back. | 09-02-2010 |
20100223929 | SYSTEM FOR FUEL INJECTION IN A TURBINE ENGINE - In an embodiment, a system includes an end cover and a liquid cartridge. The liquid cartridge is configured to mount in a fuel nozzle of a turbine engine, wherein the liquid cartridge comprises a one piece flange configured to couple to the end cover, wherein the flange comprises a water inlet, an air inlet, and a fuel inlet. | 09-09-2010 |
20100229557 | Gas turbine combustor - This invention provides a gas turbine combustor including: a main burner at a head portion of a combustor cylinder; and a pre-mixing type supplemental burner at a downstream portion of the combustor cylinder and extending through a circumferential wall thereof. The supplemental burner includes: an introducing passage configured to deflect a part of the compressed air radially inward, the compressed air flowing from an air passage between the circumferential wall of the combustor cylinder and a housing surrounding the circumferential wall toward the head portion of the combustor cylinder, and introduce the compressed air into the combustor cylinder; and a fuel nozzle configured to supply the fuel from fuel injection holes to the compressed air introduced into the introducing passage to produce a pre-mixed gas in the introducing passage. | 09-16-2010 |
20100251719 | Centerbody for mixer assembly of a gas turbine engine combustor - A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer and a centerbody positioned between the pilot mixer and the main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing. The main mixer includes: a main housing surrounding the pilot housing and defining an annular cavity; a plurality of fuel injection ports for introducing fuel into the annular cavity; and, a swirler arrangement including at least one swirler positioned upstream from the fuel injection ports, wherein each swirler of the arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and the droplets of fuel dispensed by the fuel injection ports. The centerbody includes a fuel manifold therein for providing fuel to the fuel injection ports and an air manifold therein for providing air to an aft portion of the pilot mixer and/or the aft portion of the annular cavity in the main mixer. | 10-07-2010 |
20100263381 | Premixed combustion burner for gas turbine - A premixed combustion burner for a gas turbine is provided that can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has: a fuel nozzle; a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle; and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle and that gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vane. | 10-21-2010 |
20100275601 | TURBINE AIR FLOW CONDITIONER - A system includes an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor. The air flow conditioner comprises a perforated annular wall configured to direct an air flow in both an axial direction and a radial direction relative to an axis of the turbine combustor. In addition, the air flow conditioner is configured to uniformly supply the air flow into air inlets of one or more fuel nozzles. | 11-04-2010 |
20100275602 | BURNER FOR A GAS TURBINE ENGINE - A burner for a gas turbine engine is provided. The burner includes a radial swirler for creating a swirling fuel/air mix, a combustion chamber where combustion of the swirling fuel/air mix occurs, and a pre-chamber located between the radial swirler and the combustion chamber. The radial swirler includes a plurality of vanes arranged in a circle, generally radially inwardly extending flow slots are defined between adjacent vanes in the circle, each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, and a base and top. A flow slot includes a first gas fuel injection hole in its base and a flow slot includes a second gas fuel injection hole in its first side wherein the amounts of gas fuel injected via the first and second gas fuel injection holes are independently variable. | 11-04-2010 |
20100275603 | COMBUSTOR OF GAS TURBINE - A combustor | 11-04-2010 |
20100281871 | Airblown Syngas Fuel Nozzle with Diluent Openings - A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone. | 11-11-2010 |
20100293953 | COMBUSTOR FOR A GAS-TURBINE ENGINE - A combustor for a gas-turbine engine including a burner head, a combustion chamber disposed downstream of the burner head, a swirler for creating a swirling flow of air in the combustion chamber, and a fuel nozzle disposed in the burner head. The fuel nozzle is disposed giving rise to a first angle of exit of the fuel from a downstream face of the burner head of >±0° with respect to a longitudinal axis of the combustor, this first angle lying in a first plane passing through the longitudinal axis. The fuel also exits at a second angle from the downstream face of >±0° with respect to the first plane, the second angle lying in a second plane orthogonal to the first plane. | 11-25-2010 |
20100300102 | METHOD AND APPARATUS FOR AIR AND FUEL INJECTION IN A TURBINE - A method includes receiving fuel and air into a cup of a turbine fuel nozzle. The method also includes mixing the fuel and air at least partially within the cup. In addition, the method includes directing a fuel air mixture toward a turbine combustor. The method also includes shielding an inner wall of the cup with a blanket of a protective fluid flow to reduce the possibility of flame holding along the inner wall. The protective fluid flow excludes a combustible mixture of fuel and air. | 12-02-2010 |
20100300103 | SYSTEM FOR VAPORIZATION OF LIQUID FUELS FOR COMBUSTION AND METHOD OF USE - A gas stream with a reduced oxygen concentration relative to ambient air is used to vaporize a liquid fuel or liquefied higher hydrocarbon gas, or is mixed with a vaporized gas, and the reduced oxygen vaporized fuel gas is fed to a combustion device such as a premixed or diffusion combustor. Preferably, the oxygen content of the gas stream is less than the limiting oxygen index. By mixing the fuel with a gas stream that has an appropriately reduced oxygen content, auto-ignition prior to the desired flame location in the combustor can be avoided. In some embodiments, the reduced oxygen stream is generated from an air separator or taken from the exhaust of the combustion device. | 12-02-2010 |
20100313569 | Distributed-Jet Combustion Nozzle - A combustion nozzle for use in a turbine. The combustion nozzle may include a center body and a cone extending from the center body. The cone may include a number of apertures positioned therein. | 12-16-2010 |
20110005229 | LEAN DIRECT INJECTION FOR PREMIXED PILOT APPLICATION - Embodiments of this invention provide a premixed pilot assembly for use with a fuel nozzle for a turbine. The level of nitrogen oxide (NOx) emitted by the pilot is reduced by mixing the fuel and air fast, at the end of the pilot nozzle, thereby avoiding significant zones of rich fuel and air mixtures. The air is mixed with the fuel through the use of openings in a first cylinder and a second cylinder, one of which carries air and one of which carries pilot fuel. The openings can be configured as necessary to obtain a desired effect on the pilot. | 01-13-2011 |
20110011092 | COMBUSTOR, GAS TURBINE COMBUSTOR, AND AIR SUPPLY METHOD FOR SAME - A combustor comprises a liquid fuel nozzle for injecting liquid fuel to a combustion chamber, and an air supply nozzle disposed around the liquid fuel nozzle and injecting air. The air supply nozzle is disposed such that air is injected from the air supply nozzle in a direction toward an axis of the liquid fuel nozzle. A space is formed around an outlet of the liquid fuel nozzle, through which the liquid fuel is injected from the liquid fuel nozzle to the combustion chamber, upstream of a distal end of the outlet in a direction in which the liquid fuel is injected. Carbonaceous deposits on surrounding surfaces of the outlet of the liquid fuel nozzle can be suppressed regardless of the operating conditions of a combustor. | 01-20-2011 |
20110016867 | Quarls in a Burner - A quarl of a burner for a gas turbine engine is provided. Fuel and air is mixed and provided to the burner. The quarl is arranged to house a main flame. Stability is achieved by a quarl, which is formed from a plurality of quarl sections, wherein each quarl section includes the configuration of the conical shell of a truncated cone and are distributed consecutively one after the other in the downstream direction of the burner, wherein a most narrow part of the shell of a downstream quarl section surrounds the widest part of the shell of the closest upstream quarl section and wherein an annular channel for premixed air and fuel is arranged between two consecutive quarl sections. | 01-27-2011 |
20110056205 | BURNER ARRANGEMENT AND USE OF SAME - A burner arrangement is provided including a swirl-generating premix burner for providing a fuel/air mixture produced with a first fuel as well as a mixing pipe adjoining the premix burner downstream thereof and extending into a combustion chamber. In the case of such a burner arrangement, safer operation with highly reactive, in particular H | 03-10-2011 |
20110061389 | Radial Inlet Guide Vanes for a Combustor - The present application thus provides a combustor. The combustor may include an interior flow path therethrough, a number of nozzles in communication with the interior flow path, and an inlet guide vane system positioned about the interior flow path to create a swirled flow therein. | 03-17-2011 |
20110061390 | INLET PREMIXER FOR COMBUSTION APPARATUS - A premixer is provided for injecting premixed fuel-air mixture into the inlet of a combustion apparatus. In one embodiment, the premixer assembly comprises a plurality of concentric, aerodynamic injector rings, with radially-directed injection holes. The injection holes have a plurality of different diameters, facilitating good mixing over a broad power range. Due to configuration and hole sizes, the assembly is gas or liquid compatible. The radial, concentric injection formation allows for a short injection path. | 03-17-2011 |
20110061391 | VORTEX PREMIXER FOR COMBUSTION APPARATUS - In one embodiment, a premixer is provided for use, e.g., with trapped vortex (TVC) combustors, that injects premixed fuel and air directly into the recirculating vortex, in a manner compatible with natural vortex flow in the cavity. | 03-17-2011 |
20110061392 | COMBUSTION CAVITY LAYOUTS FOR FUEL STAGING IN TRAPPED VORTEX COMBUSTORS - In one embodiment, alternative combustion cavity layouts are provided for practicing fuel staging in a trapped vortex (TVC) combustion apparatus comprising an inlet premixer, for injecting fuel-air mixture into the inlet of the combustion apparatus and one or more vortex premixers, for injecting fuel-air mixture into the recirculating vortex within each of one or more trapped vortex cavities. A plurality of TVC cavities, may, for example, be laid out axially, radially, peripherally, internally, or in combinations of such arrangements. These layouts may be used in conjunction with a fuel staging method whereby the relative proportion of mixture introduced through the inlet and the respective vortex premixers can be varied as a function of operating conditions. | 03-17-2011 |
20110083439 | Staged Multi-Tube Premixing Injector - A fuel injection nozzle includes a body member having an upstream wall opposing a downstream wall, and an internal wall disposed between the upstream wall and the downstream wall, a first chamber partially defined by the an inner surface of the upstream wall and a surface of the internal wall, a second chamber partially defined by an inner surface of the downstream wall and a surface of the internal wall a first gas inlet communicative with the first chamber operative to emit a first gas into the first chamber, a second gas inlet communicative with the second chamber operative to emit a second gas into the second chamber, and a plurality of mixing tubes, each of the mixing tubes having a tube inner surface, a tube outer surface, a first inlet communicative with an aperture in the upstream wall operative to receive a third gas. | 04-14-2011 |
20110088401 | MIXER ASSEMBLY FOR GAS TURBINE ENGINE COMBUSTOR - A mixer for a gas turbine engine combustor includes: (a) a primary fuel injector with upstream and downstream ends, the primary fuel injector including: (1) a hollow central portion configured to pass a first air stream; (2) an annular fuel passage at the downstream end, configured to discharge an annular first fuel stream surrounding the first air stream; (b) an annular splitter surrounding the primary fuel injector, configured to pass a second air stream surrounding the first fuel stream; (c) an annular first housing surrounding the splitter, and having an exit positioned axially downstream of the primary fuel injector and the splitter; and (d) fuel injection ports disposed in an array outside the first housing, and disposed in communication with a fuel supply and positioned to discharge a second fuel stream into a third air stream at a position axially upstream of the exit of the first housing. | 04-21-2011 |
20110094233 | Combustion Device and Method for Controlling Combustion Device - A combustion device includes: a combustion liner in which a combustion chamber is formed; a main burner provided at a top portion of the combustion liner and including a premix passage configured to annularly inject a pre-mixed gas of a fuel and air into the combustion chamber and a radial swirler configured to introduce the fuel and the air to the premix passage in a radially inward direction; and a fuel injection pipe configured to inject the fuel to the radial swirler from an entrance side of the radial swirler, and the radial swirler is divided into a plurality of swirler stages by dividing plates in an axial direction. | 04-28-2011 |
20110107763 | MICRO-TURBINE COMBUSTOR - A micro gas turbine engine for use in a turbo heater or co-generation application is described. The micro gas turbine engine includes a fuel delivery system which minimizes the development of deposits in the air-fuel passageway. To this end, a fuel delivery channel formed between a fuel deflector and a slinger body is formed with a contoured or undulating surface. A fuel deflector ring is interposed between the fuel delivery channel and the slinger impeller to facilitate the flow of the air-fuel mixture into the combustion chamber. | 05-12-2011 |
20110107764 | FUEL NOZZLE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME - A method of assembling a fuel nozzle assembly for a gas turbine engine having a natural operating frequency includes providing a flange and providing a premix tube. The flange is fabricated from a first alloy such that the flange is configured to exhibit a first frequency that is different than the natural operating frequency of the gas turbine engine. The premix tube is fabricated from a second alloy such that the premix tube is configured to exhibit a second frequency that is different from the natural operating frequency of the gas turbine engine. The premix tube is coupled to the flange. | 05-12-2011 |
20110113784 | Swirler Vane, Swirler and Burner Assembly - A swirler vane for providing fuel, particularly liquid fuel, to a swirling zone of a burner assembly is provided. The swirler vane includes at least one injection hole for injecting the fuel to the swirling zone of the burner and an injection feed hole passage connecting the at least one injection hole with a main fuel feed. The swirler vane or a tip of the swirler vane, where the at least one injection hole is arranged, is manufactured by laser deposition or includes at least a surface manufactured by laser deposition. A swirler including a plurality of such swirler vanes and a burner assembly including the swirler with such swirler vanes are also provided. | 05-19-2011 |
20110131998 | FUEL INJECTION IN SECONDARY FUEL NOZZLE - In a conventional secondary fuel nozzle for a gas turbine combustion system, secondary air enters and flows around pegs to mix with fuel injected through holes in pegs. Because the pegs are in the air flow area, undesirable pressure drops occur adversely affecting turbine's efficiency and leading to higher emissions. A novel secondary fuel nozzle is provided in which fuel is injected upstream of the secondary air entry location, which allows the pegs to be removed from the flow area. An example secondary fuel nozzle includes a nozzle body delivering fuel, a nozzle housing surrounding the nozzle body and defining air passages for the secondary air to enter and flow toward an end of the nozzle body, and a premix fuel unit positioned upstream of the air passages injecting fuel delivered by the nozzle body into the secondary air for premixing prior to combustion. | 06-09-2011 |
20110146284 | Plate-like-object manufacturing method, plate-like objects, gas-turbine combustor, and gas turbine - A plate-like-object manufacturing method, plate-like objects, a gas-turbine combustor, and a gas turbine, in which degradation in the cooling performance can be suppressed, the time required for manufacturing a gas-turbine combustor can be shortened, and deterioration of the working environment can be prevented are provided. A plate-like-object manufacturing method includes a step of forming a plate-like object by stacking a plurality of plates and arranging a plurality of channels, through which a cooling medium flows, side-by-side between the plurality of plates; and a step of arranging a plurality of the plate-like objects side-by-side in a direction in which the channels are arranged, butting the plurality of plate-like objects against each other, and performing welding at an abutment section. The channels adjacent to the abutment section extend along the abutment section and have a greater dimension in the direction in which the channels are arranged, as compared with that of other channels. | 06-23-2011 |
20110162371 | Fuel Nozzle with Integrated Passages and Method of Operation - Disclosed is a method of operating a secondary fuel nozzle for a turbomachine combustor including delivering a flow of pilot fuel through a pilot fuel channel toward a combustion zone and delivering a flow of air through a plurality of transfer passages arranged around the pilot fuel channel toward the combustion zone. The flow of pilot fuel and the flow of air are combusted in the combustion zone, and a flow of transfer fuel is delivered through the plurality of transfer passages for combustion. A secondary fuel nozzle includes a pilot fuel channel extending along the fuel nozzle to deliver a flow of pilot fuel to a combustion zone. A plurality of transfer passages are arranged around the pilot fuel channel and are configured to deliver a flow of air for combustion with the flow of pilot fuel and to deliver a flow of transfer fuel to the combustion zone. | 07-07-2011 |
20110203283 | Burner arrangement - A burner arrangement is provided. The burner arrangement includes a support as well as at least two fuel nozzles, with fuel nozzle tips, attached to the support in the direction of flow and a gas feed system to the fuel nozzle tips extending through the support. Each fuel nozzle includes a support-side section which on the support side includes a contact surface with which the fuel nozzle rests on a supporting surface of the support, at least two fuel nozzle tips formed in one piece running from the support-side section in the direction of flow, the gas feed system including at least one gas feed line and its lead-through through the support, the lead-through being embodied as a fit. | 08-25-2011 |
20110225973 | Combustor with Pre-Mixing Primary Fuel-Nozzle Assembly - A combustor includes a first combustion chamber, a pre-mixing primary fuel-nozzle assembly associated with the first combustion chamber, a second combustion chamber, and a secondary fuel-nozzle assembly associated with the second combustion chamber. The pre-mixing primary fuel-nozzle assembly includes a number of vanes configured to swirl airflow, each vane comprising a number of fuel injection holes configured to inject fuel into the airflow. | 09-22-2011 |
20110239652 | SEGMENTED ANNULAR RING-MANIFOLD QUATERNARY FUEL DISTRIBUTOR - A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support. | 10-06-2011 |
20110252802 | COANNULAR OIL INJECTION NOZZLE - A premixer is provided and includes a peripheral wall defining a mixing chamber therein through which a flow path for a fluid is defined, a nozzle including an annular splitter plate disposed in the flow path within the mixing chamber, the splitter plate including a trailing edge defined in relation to a predominant direction of fluid flow along the flow path and being formed to define a fuel line therein, which is receptive of oil fuel and an annular array of fuel injectors disposed at the trailing edge, which are each fluidly communicative with the fuel line and configured to inject at least the oil fuel into the flow path with the oil fuel being substantially atomized upon injection or substantially immediately after the injection by interaction with the fluid flowing along the flow path. | 10-20-2011 |
20110271680 | LEAN PREMIX BURNER OF A GAS-TURBINE ENGINE PROVIDED WITH A CONCENTRIC ANNULAR CENTRAL BODY - This invention relates to a lean premix burner of a gas-turbine engine with an annular central body | 11-10-2011 |
20110271681 | LEAN PREMIX BURNER OF A GAS-TURBINE ENGINE PROVIDED WITH A FLOW-GUIDING ELEMENT - This invention relates to a lean premix burner of a gas-turbine engine with an annular central body | 11-10-2011 |
20110271682 | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL INTO A TURBOMACHINE COMBUSTION CHAMBER - A device for injecting a mixture of air and fuel into a turbomachine combustion chamber includes a centering ring for centering an injector and a primary swirler situated downstream from the ring, the ring including axial air-passing orifices and the swirler including curved air-passing channels, a number of orifices in the ring being no greater than a number of channels in the swirler, and downstream outlets of the orifices in the ring being situated between the channels in the swirler. | 11-10-2011 |
20110277481 | LATE LEAN INJECTION INJECTOR - A fuel injector is provided and includes an outer body, a converging tubular body including a converging section, defining a converging annular passage therein and being disposed within the outer body to define an outer annular passage between an interior surface of the outer body and an exterior surface of the converging tubular body, the annular passages each being receptive of a fluid at respective inlets thereof such that the fluid is directed to flow toward respective outlets thereof and a fuel line to deliver fuel through at least the converging tubular body at the converging section to the converging annular passage in a substantially tangential direction relative to a circumferential curvature of the converging tubular body. | 11-17-2011 |
20110296839 | Self-Regulating Fuel Staging Port for Turbine Combustor | 12-08-2011 |
20110314823 | GAS TURBINE COMBUSTOR LINER CAP ASSEMBLY - A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate. | 12-29-2011 |
20110314824 | SWIRLER, FUEL AND AIR ASSEMBLY AND COMBUSTOR - An air swirler, a fuel and air admission assembly, and a staged combustor are disclosed. The staged combustor may be equipped with the fuel and air admission assemblies incorporating the air swirlers for use in gas turbine engines, such as for example gas turbine engines powering aircraft having supersonic cruise capability. | 12-29-2011 |
20110314825 | GAS TURBINE SYSTEM HAVING PREMIXED INJECTOR VANES - In certain exemplary embodiments, a system includes an annular duct having an inner annular wall and an outer annular wall. The system also includes a plurality of injector vanes configured to mix air and fuel to produce an air-fuel mixture, and configured to inject the air-fuel mixture into a central chamber between the inner and outer annular walls. | 12-29-2011 |
20120006029 | AIR BIASING SYSTEM IN A GAS TURBINE COMBUSTOR - A combustor ( | 01-12-2012 |
20120006030 | INJECTION NOZZLE FOR A TURBOMACHINE - A turbomachine includes a compressor, a combustor operatively connected to the compressor, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a first end portion that extends to a second end portion, and a plurality of tube elements provided at the second end portion. Each of the plurality of tube elements defining a fluid passage includes a body having a first end section that extends to a second end section. The second end section projects beyond the second end portion of the injection nozzle assembly. | 01-12-2012 |
20120017595 | SWIRLER, COMBUSTION CHAMBER, AND GAS TURBINE WITH IMPROVED SWIRL - A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes positioned radially around a central axis of the swirler and a plurality of mixing channels for mixing fuel and air. At least one mixing channel of the plurality of mixing channels is defined by opposite walls of two adjacent vanes of the plurality of vanes. The at least one mixing channel includes at least one fuel injection opening arranged at an upstream sections of the at least one mixing channel. The at least one mixing channel also includes an axial swirler arranged at a downstream section of the at least one mixing channel. | 01-26-2012 |
20120036855 | BURNER - A burner with a burner head is provided. The burner includes a mixing tube for premixing combustion air and fuel. The mixing tube is provided with a pilot burner system in its downstream part. The pilot burner system includes an annular mixing cavity with an entrance for assist air and pilot fuel and outlet nozzles. The mixing cavity is provided with at least two swirler wings arranged in the vicinity of each outlet nozzle. | 02-16-2012 |
20120042655 | Swirler, combustion chamber, and gas turbine with improved mixing - A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes positioned radially around a central axis of the swirler and a plurality of mixing channels for mixing the fuel and the air. At least one mixing channel of the plurality of mixing channels is defined by opposite walls of two adjacent vanes of the plurality of vanes and is comprising at least one fuel injection opening and is further comprising at least one dimple for generating a vortex of the air. Further, a combustion chamber incorporating such a swirler and a gas turbine incorporating such a combustion chamber are provided. | 02-23-2012 |
20120055161 | Method and Apparatus for Controlling Gas Turbine Combustor - An apparatus for controlling a gas turbine combustor having a diffusion combustion burner and a premix combustion burner comprising: a rotating speed detector for detecting a rotating speed of gas turbine, a recorder for recording the detected value of the rotating speed of gas turbine detected by the rotating speed detector, an arithmetic unit for calculating a change with time of the rotating speed of gas turbine in accordance with details of the detected value of the rotating speed of gas turbine recorded in the recorder, and a fuel control unit for judging a starting situation of reduction in the rotating speed of gas turbine on the basis of the change with time of the rotating speed of gas turbine calculated by the arithmetic unit and controlling respectively a fuel flow rate for the diffusion combustion burner to be fed to the diffusion combustion burner installed in the gas turbine combustor and a fuel flow rate for the premix combustion to be fed to the premix combustion burner. | 03-08-2012 |
20120079827 | AIR-COOLED SWIRLERHEAD - A combustor for a gas turbine engine is disclosed which is able to operate with high combustion efficiency, and low nitrous oxide emissions during gas turbine operations. The combustor consists of a can-type configuration which combusts fuel premixed with air and delivers the hot gases to a turbine. Fuel is premixed with air through a swirler and is delivered to the combustor with a high degree of swirl motion about a central axis. This swirling mixture of reactants is conveyed downstream through a flow path that expands; the mixture reacts, and establishes an upstream central recirculation flow along the central axis. A cooling assembly is located on the swirler co-linear with the central axis in which cooler air is conveyed into the prechamber between the recirculation flow and the swirler surface. | 04-05-2012 |
20120096866 | FUEL NOZZLE FOR COMBUSTOR - A nozzle for a combustor is disclosed. The nozzle includes a center body, a burner tube provided around the center body and defining a fuel-air mixing passage therebetween, and an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween. The nozzle further includes a nozzle tip connected to the center body. The nozzle tip includes a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone, and a plurality of transfer passages. The plurality of transfer passages are configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone. | 04-26-2012 |
20120102957 | PREMIXING NOZZLE - A premixing nozzle of a combustor is provided and includes a gas premixer module, a centerbody, which is breech-loadable into the gas premixer module and a deformable, compliant interface between the gas premixer module and the centerbody. | 05-03-2012 |
20120111012 | Ultra low emissions gas turbine combustor - The gaseous fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the-liner also defining inner combustion and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A fuel/air mixing apparatus disposed at the closed housing end includes a plurality of swirl vanes defining passages each having constant cross-section flow areas along the vanes, and an increasing aspect ratio from the passage inlet to the outlet. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner cools the portion of the liner defining the combustion zone. Channeling apparatus is disposed between a downstream end region of the sleeve and the mixing apparatus and includes a diffuser section with a ratio of the outlet flow area to the inlet flow area in a range of 1.3-1.5. | 05-10-2012 |
20120111013 | SYSTEM FOR DIRECTING AIR FLOW IN A FUEL NOZZLE ASSEMBLY - According to various embodiments, a system includes a fuel nozzle assembly. The fuel nozzle assembly includes a hub, a shroud disposed about the hub, a flow sleeve disposed about the shroud, and an air flow path extending between the flow sleeve and the shroud in an upstream direction toward an opening region between the shroud and the hub, wherein the air flow path extends between the hub and the shroud in a downstream direction from the opening region toward an outlet region of the fuel nozzle assembly. The fuel nozzle assembly also includes a fuel flow path extending to at least one fuel port along the air flow path, and a flow guide disposed along the air flow path in the opening region, wherein the flow guide includes a first guide portion configured to guide an air flow radially outward from the hub toward the shroud. | 05-10-2012 |
20120125004 | COMBUSTOR PREMIXER - A combustor premixer is provided and includes a burner tube having a bell mouth-shaped opening, a plurality of tubular bodies telescopically disposed within the burner tube to deliver combustible materials to a premixing passage defined between the burner tube and an outermost one of the plurality of tubular bodies and a plurality of swirler vanes arrayed circumferentially in the opening, each one of the plurality of swirler vanes including a body extending along a radial dimension from the burner tube to the outermost tubular body and a leading edge protruding upstream from the opening. | 05-24-2012 |
20120137694 | BURNER AND GAS TURBINE COMBUSTOR - A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet. | 06-07-2012 |
20120144832 | PASSIVE AIR-FUEL MIXING PRECHAMBER - A gas turbine combustion system passive air-fuel mixing prechamber includes one or more fuel passages. Each fuel passage includes at least one downstream fuel injection orifice. One or more fluid conduits connect an upstream portion of at least one fuel passage with one or more air passages such that pressure drops across each fuel injection orifice substantially self-equalize in a passive manner with corresponding air passage pressure drops over a broad range of fuel lower heating value (LHV) from about 150 Btu/scf to about 900 Btu/scf of fuel passing through the fuel passage while mixing with air passing through one or more connected fluid conduits. The effective area of each fluid conduit relative to the corresponding fuel and air passages is dependent upon the desired fuel LHV operating range. | 06-14-2012 |
20120151927 | PEGLESS SECONDARY FUEL NOZZLE - A unitary fuel injection manifold for a secondary fuel nozzle improves fuel-air mixing and offers flexibility to alter the mixing profile through adaptability to a variety of number, types, and orientation of discharge outlets to the combustion air mixing space around the secondary fuel nozzle. An aerodynamic surface with reduced extension into the mixing space reduces pressures drop and interference with design airflow. Manifold integrity is enhanced by elimination of fillet welds to mount external pegs. | 06-21-2012 |
20120151928 | COOLING FLOWPATH DIRT DEFLECTOR IN FUEL NOZZLE - A fuel nozzle assembly includes a chamfered leading edge of an annular wall section disposed between an outer pilot swirler and an inlet to an injector cooling flowpath surrounding the second pilot swirler. A radially inwardly facing conical chamfered surface of the chamfered leading edge deflects dirt from cooling flowpath. | 06-21-2012 |
20120167570 | SCULPTED TRAILING EDGE SWIRLER COMBUSTION PREMIXER AND METHOD - Methods and devices useable in turbo-engines premixing of compressed air and fuel are provided. A premixer has a mixing part configured to receive a gas flow input in a flow direction and fluid fuel injected substantially perpendicular to the flow direction. The mixing part has a rim configured to define a substantially cylindrical shape. The mixing part also has a swirler with (i) a center body located substantially in a middle of the cylindrical shape along the flow direction, and (ii) a set of vanes extending from the center body towards the rim, the vanes being configured to determine a rotation motion inside a flow that includes the received gas flow and the injected fuel when the flow passes through the mixing part, at least some of the vanes having a trailing edge with a waving profile configured to generate mixing zones inside the flow thereafter. | 07-05-2012 |
20120180487 | SYSTEM FOR FLOW CONTROL IN MULTI-TUBE FUEL NOZZLE - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes a fuel conduit, a fuel chamber coupled to the fuel conduit, and multiple tubes concentrically arranged in multiple rows about a central axis of the multi-tube fuel nozzle and extending through the fuel chamber to a downstream end portion of the multi-tube fuel nozzle. The multiple tubes include fluids flow and different flow control features including at least one of different fuel/air premixing ratios, different tube diameters, or different outlet distances relative to the downstream end portion. | 07-19-2012 |
20120186256 | MIXER ASSEMBLY FOR A GAS TURBINE ENGINE - A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler. | 07-26-2012 |
20120192565 | SYSTEM FOR PREMIXING AIR AND FUEL IN A FUEL NOZZLE - According to various embodiments, a system includes a turbine fuel nozzle. The turbine fuel nozzle includes a first fuel passage extending to a downstream mixing region, a first air passage extending from an exterior of the turbine fuel nozzle to the downstream mixing region, and a second fuel passage extending into the first air passage upstream of the downstream mixing region. | 08-02-2012 |
20120204567 | FUEL MIXING DEVICE FOR TURBINE ENGINE COMBUSTION CHAMBER COMPRISING IMPROVED AIR FEED MEANS - A fuel mixing device for an annular combustion chamber of a turbine engine, including a member for centering a turbine engine injector head, at least one air intake ring including blades allowing swirling of air, a bowl including an annular row of air intake orifices, an annular cavity communicating with the air intake orifices, and channels arranged through the blades to feed air to the annular cavity. | 08-16-2012 |
20120227407 | BURNER FOR A TURBINE - A burner for a turbine has a flame tube, a casing enclosing the flame tube forming an oxidant collection chamber, a burner bottom which bounds the oxidant collection chamber and the combustion space, and a swirler which has a plurality of guide vanes arranged so that the distances between the guide vanes form a plurality of radial inlet passages to the combustion space. A fuel supply pipe is provided in the inlet flow region of at least some of the inlet passages, which fuel supply pipe extends lengthwise through the respective inlet passage in an axial direction of the burner and traverse to an oxidant flow direction, and wherein each fuel supply pipe has in its wall at least one radial fuel output opening by which fuel can be mixed into the respective inlet passage with a directional component extending transverse to the oxidant flow direction. | 09-13-2012 |
20120234010 | BURNER ASSEMBLY - A burner assembly having a fuel distribution ring, number of fuel nozzles which are mounted on the fuel distribution ring in the direction of low is provided. The fuel distribution ring has a ring-shaped surface in the direction of flow and wherein the fuel distribution ring center and an opposite outer outer side and wherein there is at least one slot on the surface between the fuel nozzles and the at least one slot extends on the surface from the outside to the inside. There is at least one recess arranged on the surface and the at least one recess also partially includes the outside of the fuel distributor. | 09-20-2012 |
20120247110 | DEVICE FOR MIXING FUEL AND AIR OF A JET ENGINE - A device for mixing fuel and air of a jet engine includes at least one air-carrying duct and at least one further fuel-carrying duct. Guide elements extending over the duct height and distributed over the circumference of the duct are provided at least in the air-carrying duct, in the area of which guide elements a twist can be imparted to the air flowing in the air-carrying duct in order to improve mixing between the air and the fuel downstream of the ducts. The guide elements are provided at a trailing edge with at least one downstream extending projection and/or upstream extending recess designed at least approximately or at least in some areas with a sharp edge. | 10-04-2012 |
20120285172 | PREMIXED BURNER FOR A GAS TURBINE COMBUSTOR - The disclosure relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, wherein the at least one body is located in a first section of the burner with a first cross-sectional area at a leading edge of the at least one body with reference to a main flow direction prevailing in the burner, wherein downstream of said body a mixing zone is located with a second cross-sectional area, and at and/or downstream of said body the cross-sectional area is reduced, such that the first cross-sectional area is larger than the second cross-sectional area. | 11-15-2012 |
20120291439 | LEAN DIRECT FUEL INJECTOR - A dual fuel injector for a gas turbine engine includes a central cavity extending along a longitudinal axis from a first end to a second end, and a first fuel discharge outlet configured to direct a first fuel into the central cavity at the first end. The fuel injector may also include a first air discharge opening circumferentially disposed about the first fuel discharge outlet and configured to direct a first quantity of air into the central cavity, and a second air discharge opening circumferentially disposed about the central cavity and configured to discharge a second quantity of air into the central cavity downstream of the first air discharge outlet. The fuel injector may further include a second fuel discharge outlet circumferentially disposed about the central cavity and configured to discharge a second fuel therethrough. The second fuel may be different from the first fuel. | 11-22-2012 |
20120291440 | GAS TURBINE COMBUSTION CAP ASSEMBLY - A gas turbine combustor cap assembly ( | 11-22-2012 |
20120291441 | INJECTOR DEVICE AND COMBUSTION CHAMBER FOR A TURBOMACHINE PROVIDED WITH SUCH INJECTOR DEVICE - A low-cost combustion chamber injector device that has sturdier construction and is safer for use. Parts are configured specifically to be nested, to dispense with welding between the cellular parts. The device for injecting a fuel-air mix includes, centered on a single axis, a swirl chamber including at least two annular air suction parts, a centering guide, and a retainer ring. The annular parts have cellular conduits connecting to axial inner and outer Venturi tubes. The parts are coaxially mounted, the inner part being configured to be self-centered in the outer part by engagement of the axial and radial walls and then, after assembly, the outer part is welded to the retainer ring and to the inner part in a single radial plane. | 11-22-2012 |
20120297777 | REHEAT BURNER INJECTION SYSTEM WITH FUEL LANCES - The disclosure relates to a burner such as for a secondary combustion chamber of a gas turbine with sequential combustion having a first and a second combustion chamber, with an injection device for introduction of at least one gaseous and/or liquid fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one gaseous fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. At least one nozzle has its outlet orifice downstream of a trailing edge of the streamlined body. | 11-29-2012 |
20120304648 | INTEGRATED LATE LEAN INJECTION ON A COMBUSTION LINER AND LATE LEAN INJECTION SLEEVE ASSEMBLY - A late lean injection sleeve assembly allows the injection of fuel at the aft end of a gas turbine liner, before the transition piece, into the combustion gases downstream of a turbine combustor's fuel nozzles. The late lean injection enables fuel injection downstream of the fuel nozzles to create a secondary/tertiary (with quaternary injection upstream of the fuel nozzles) combustion zone while reducing/eliminating the risk of fuel leaking into the combustion discharge case. The fuel is delivered by the flow sleeve into one or more nozzles that mix the fuel with CDC air before injecting it into the combustor's liner. | 12-06-2012 |
20120304649 | FUEL INJECTOR - A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the main injector includes: a first inflow channel through which the air having a major flow component in an axial direction is taken; a second inflow channel through which the air having a major flow component in a radial direction is taken and which causes the air therein to meet the air from the first inflow channel; and a main fuel injecting portion configured to inject the fuel only to the second inflow channel. | 12-06-2012 |
20120304650 | INJECTION SYSTEM FOR A TURBOMACHINE COMBUSTION CHAMBER, INCLUDING AIR INJECTION MEANS IMPROVING THE AIR-FUEL MIXTURE - An air and fuel injection system for the back of a turbomachine's annular combustion chamber, including a central injector and a peripheral annular fuel injector including at least one fuel injection aperture made in an annular wall and emerging in a peripheral annular channel separated from a central channel by the annular wall and having an annular space of admission of air. The system also includes multiple air ejection apertures made in the annular wall downstream from the fuel ejection aperture or apertures in reference to the flow of the air stream, for an additional injection of air into the channel. | 12-06-2012 |
20120324896 | PREMIXER FUEL NOZZLE FOR GAS TURBINE ENGINE - In an embodiment, a system includes a turbine fuel nozzle having a hub with an axis, a shroud surrounding the hub along the axis, an air flow path between the hub and the shroud, and a fuel flow path. The turbine fuel nozzle also includes a swirl vane extending between the hub and the shroud in a radial direction relative to the axis. The swirl vane includes a fuel inlet coupled to the fuel flow path, a fuel chamber extending from the fuel inlet, and a plurality of fuel outlets extending from the fuel chamber to the air flow path. The plurality of fuel outlets is positioned at an axial distance of at least approximately â…” of an axial length of the fuel chamber downstream from an upstream point along an upstream edge of the fuel chamber. | 12-27-2012 |
20130000307 | SWIRLER FOR GAS TURBINE ENGINE FUEL INJECTOR - A swirler for fuel injection in a gas turbine engine includes a frustoconical swirler body. A first and a second air flow path direct air in generally opposed circumferential directions into the swirler. These air paths intermix and create turbulence. As this turbulence encounters fuel droplets, the fuel is atomized, and uniformly distributed within the air flow. A shear layer is created adjacent an inner surface of the swirler body. In a separate feature, a third air flow path is directed into the air. | 01-03-2013 |
20130025283 | SECTOR NOZZLE MOUNTING SYSTEMS - Systems are provided for mounting sector nozzles within gas turbine combustors. In one embodiment, a sector nozzle includes a nozzle portion configured to mix fuel and air to produce a fuel-air mixture and a shell coupled to the nozzle portion. The sector nozzle also includes a first longitudinal strut and a second longitudinal strut coupled to a first surface of the shell on opposite sides of a window within the first surface. A third longitudinal strut is coupled to a second surface of the shell, and the second surface is disposed opposite of the first surface. | 01-31-2013 |
20130025284 | PREMIXING APPARATUS FOR GAS TURBINE SYSTEM - A premixing apparatus for a gas turbine system includes non-swirl elements around a periphery of a face of a premixing apparatus and a swirl assembly located substantially at a center of the face. The non-swirl elements premix a premixture prior to the premixture being delivered to a combustor of the gas turbine system. The swirl assembly disturbs a flow of fluid prior to the fluid being delivered to the combustor. The premixture includes fuel and oxidant, and the fluid disturbed by the swirl assembly includes the oxidant or the premixture. | 01-31-2013 |
20130031905 | FUEL NOZZLE - A fuel nozzle is provided and includes a nozzle body defining first and second interior regions for providing a supply of first and second fluids, a collar defining a third interior region and radial slots permitting radial ingress of a third fluid to the third interior region and a nozzle tip interposed between the nozzle body and the collar. The nozzle tip defines an annular slot, first discrete passageways by which the first fluid is communicated from the first interior region to the annular slot, second discrete passageways by which the first fluid is communicated from the annular slot to the radial slots, and third discrete passageways by which the second fluid is communicated from the second interior region to the radial slots. | 02-07-2013 |
20130031906 | ASSEMBLIES AND APPARATUS RELATED TO INTEGRATING LATE LEAN INJECTION INTO COMBUSTION TURBINE ENGINES - An assembly for use in a late lean injection system of a combustor of a combustion turbine engine, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the assembly comprising: a boss rigidly secured to the inner radial wall, the boss being configured to define a hollow passageway through the inner radial wall; a transfer tube slideably engaged within the boss; a stop formed on the transfer tube; and damping means positioned between the boss and the stop. | 02-07-2013 |
20130086910 | SYSTEM FOR FUEL INJECTION IN A FUEL NOZZLE - A system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets. | 04-11-2013 |
20130091846 | INJECTOR HAVING MULTIPLE FUEL PEGS - A fuel injector is provided, including a fuel injector body, a plurality of fuel vanes, and a plurality of fuel pegs. The injector body includes a manifold and an inlet. The manifold is configured for receiving fuel, and the inlet is configured for receiving air. The fuel vanes are located within the injector body and are positioned in a direction that is generally parallel with a longitudinal axis of the injector body to orient the air flowing from the inlet. The plurality of fuel pegs are fluidly connected to the manifold and are arranged within the plurality of fuel vanes. The plurality of fuel pegs are each spaced at a distance that is about equal between each of the plurality of fuel pegs. | 04-18-2013 |
20130125549 | GAS TURBINE COMBUSTOR ENDCOVER WITH ADJUSTABLE FLOW RESTRICTOR AND RELATED METHOD - An endcover for a turbine combustor adapted to support one or more combustor nozzles, includes a plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel cavity is formed in the plate; and a fuel restrictor insert is formed with at least one flow orifice located within the fuel cavity for supplying fuel to at least one combustor nozzle. The fuel restrictor insert is adjustable along a length dimension of the fuel cavity. | 05-23-2013 |
20130133329 | AIR FUEL PREMIXER HAVING ARRAYED MIXING VANES FOR GAS TURBINE COMBUSTOR - A fuel-air premixer for use in a combustor of a gas turbine includes an air inlet, a fuel inlet, a shroud, a central body and a cascade of vanes. The premixer mixes fuel and air in the annular mixing passage into a uniform mixture for injecting into a combustor reaction zone. The air from a compressor is injected into the mixer through an air inlet. The fuel is introduced into air stream via fuel injection holes that pass through the walls of the vanes which contain internal fuel flow passages. The flow field inside the premixer is broken up by the arrayed vanes into a series of small regions each containing a well designed small size mixing eddy which is steadily attached to the surface of the vanes. | 05-30-2013 |
20130145765 | SYSTEM FOR AERODYNAMICALLY ENHANCED PREMIXER FOR REDUCED EMISSIONS - A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer. | 06-13-2013 |
20130167539 | FUEL NOZZLES FOR INJECTING FUEL IN A GAS TURBINE COMBUSTOR - Fuel nozzles for gas turbines are provided that include liquid fuel cartridges. In one embodiment, a fuel nozzle includes a fuel plenum plate separating an air plenum from a fuel plenum. The fuel nozzle also includes a plurality of mixing tubes extending through the fuel plenum from the fuel plenum plate to a face plate. Each mixing tube includes an air inlet configured to receive air from the air plenum, a fuel inlet disposed in a tube wall within the fuel plenum to direct fuel from the fuel plenum into the mixing tube to produce a fuel-air mixture, and a fuel-air outlet configured to discharge the fuel-air mixture away from the face plate into a combustion region. The fuel nozzle further includes a liquid fuel cartridge extending through the air plenum and the fuel plenum to the face plate. The liquid fuel cartridge includes a liquid fuel passage. | 07-04-2013 |
20130167540 | COMBUSTOR OF A TURBOMACHINE - A combustor of a turbomachine is provided and includes an assembly defining an interior and being configured to direct air to flow along an annulus in a first direction about the interior and in a second direction toward the interior, the first and second directions being substantially opposed, a manifold configured to be supplied with fuel and a tubular body defining a pathway along which the air is transmittable in a third direction from the annulus to the interior, the third direction being transverse to the first and second directions. The tubular body includes a sidewall extendible through the manifold. The sidewall defines an injection hole within the manifold by which transmitted air is mixable with the fuel. | 07-04-2013 |
20130174559 | SYMMETRIC FUEL INJECTION FOR TURBINE COMBUSTOR - A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture. | 07-11-2013 |
20130174560 | COMBUSTOR ASSEMBLY IN A GAS TURBINE ENGINE - A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct. | 07-11-2013 |
20130180248 | Combustor Nozzle/Premixer with Curved Sections - An apparatus for premixing fuel and air prior to combustion in a gas turbine engine includes an annular fuel passage receiving fuel from a fuel source. The annular fuel passage includes a fuel plenum and has a wave shape with a peak section surrounded by trough sections. An annular air passage surrounds the annular fuel passage. The annular air passage receives air to be mixed with the fuel in the fuel passage for downstream combustion. A plurality of swirler vanes are disposed in the annular air passage adjacent the fuel plenum. | 07-18-2013 |
20130186092 | MICROMIXER OF TURBINE SYSTEM - A micromixer of a turbine system is provided and the micromixer includes a plurality of pipes each having an inlet and an outlet for receiving flow and dispersing the flow to a combustor. Also provided is a non-uniform inlet arrangement defined by the inlets of the plurality of pipes, wherein at least one of the inlets extends to an axial location distinct from at least one other inlet. | 07-25-2013 |
20130199188 | Combustor Assembly with Trapped Vortex Cavity - Embodiments of the present application include a combustor assembly. The combustor assembly may include an annular trapped vortex cavity located adjacent to a downstream end of a bundle of air/fuel premixing injection tubes. The annular trapped vortex cavity may include an opening at a radially inner portion of the annular trapped vortex cavity adjacent to the head end of the bundle of premixing tubes. The annular trapped vortex cavity may also include one or more air injection holes and one or more fuel sources disposed about the annular trapped vortex cavity such that the one or more air injection holes and the one or more fuel sources are configured to drive a vortex within the annular trapped vortex cavity. | 08-08-2013 |
20130199189 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes a plurality of tube assemblies wherein each of the plurality of tube assemblies includes a plurality of tubes. At least one injection system is coupled to at least one tube assembly of the plurality of tube assemblies. The injection system includes a fluid supply member that is positioned a predefined distance upstream from the tube assembly. The fluid supply member includes a first portion that includes at least one first opening for delivering fluid toward the tube assembly for reducing dynamic pressure oscillations within a combustor and/or reducing NOx emission within the combustor during operation of the turbine engine. | 08-08-2013 |
20130205788 | UNKNOWN - The present invention relates to a premix burner of a combustion chamber of a gas turbine with at least one annular duct for supplying air and fuel, including a radially outer and a radially inner combustion chamber wall relative to a burner central axis and with at least one swirler arranged in the duct, said swirler including several flow-guiding elements distributed around the circumference of the duct cross-section, characterized in that at least one radially inner duct wall is provided in the area of the flow-guiding elements with a concave recess of the annular groove type. | 08-15-2013 |
20130213045 | Coated Porous Metallic Mat - A porous metallic mat is provided. The porous metallic mat includes a plurality of fibers and a protective coating. The plurality of fibers is sintered into a mat configuration. The protective coating is provided on the porous metallic mat. The protective coating includes a diffusion aluminide configured to provide oxidation resistance to the porous metallic mat. | 08-22-2013 |
20130219896 | FLAME HOLDING BOUNDARY CONTROL - A power plant control system monitors a flame holding boundary indicator, such as Damköhler number, to determine a lowest amount of a quenching agent that can prevent flame holding in a predefined region of a gas turbine. In embodiments, the amount of quenching agent used may be minimized to reduce operating costs while ensuring safe operation of the gas turbine. | 08-29-2013 |
20130219897 | COMBUSTOR AND GAS TURBINE - The combustor of the present invention is provided with a combustor basket to which air A is supplied from outside, first nozzles which are installed in a plural number annularly along an inner circumference of the combustor basket to individually supply premixed gas M of the air (A) with a fuel (f) into the combustor basket, and a transition piece, a base end of which is connected to the combustor basket, and which burns the premixed gas (M) supplied from the first nozzles to form a flame front (F) which spreads to an outer circumference toward the leading end in an axial direction. Each of the first nozzles supplies the premixed gas (M) by changing the fuel concentration around the center axis of the first nozzle so that the flame front (F) is made uniform in temperature in the axial direction. | 08-29-2013 |
20130219898 | COMBUSTOR AND GAS TURBINE - A combustor according to the invention includes a combustor basket to which air A is supplied from the outside, a plurality of first nozzles that are annularly provided along the inner periphery of the combustor basket and that supply premixed gas M of the air and fuel to the inside of the combustor basket, and a transition piece in which the combustor basket is connected to a base end thereof and which burns the premixed gas supplied from the first nozzles, thereby forming a flame front spread to the outer periphery side toward the leading end in an axial direction, wherein each first nozzle supplies the premixed gas with fuel concentration changed around the center axis of the first nozzle such that the flame front has a uniform temperature in the axial direction. | 08-29-2013 |
20130227951 | LASER CLAD FUEL INJECTOR PREMIX BARREL - A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling. | 09-05-2013 |
20130232977 | FUEL NOZZLE AND A COMBUSTOR FOR A GAS TURBINE - A fuel nozzle for a gas turbine includes an annular passage configured to flow a fuel and a disk concentric with and disposed at a second end of the annular passage. The disk extends radially outward from the second end. A plurality of passages extend through the disk and are configured to impart swirl to a working fluid flowing through the passages. A shroud including an upstream end axially separated from a downstream end surrounds the disk and extends downstream from the disk. | 09-12-2013 |
20130232978 | FUEL AIR PREMIXER FOR GAS TURBINE ENGINE - A fuel-air premixer for a combustor of a turbine engine includes a central passage along an axis. The central passage is operable to communicate an unswirled airflow. An outer annular passage is located around the axis and includes a multiple of first swirl vanes that are operable to communicate a first swirled airflow in a first direction. An inner annular passage is located around the axis between the central passage and the outer annular passage. The inner annular passage includes a multiple of second swirl vanes that are operable to communicate a second swirled airflow in a second direction different than the first direction. | 09-12-2013 |
20130232979 | SYSTEM FOR ENHANCING MIXING IN A MULTI-TUBE FUEL NOZZLE - A system includes a multi-tube fuel nozzle including a fuel nozzle head and multiple tubes. The fuel nozzle head includes an outer wall surrounding a chamber, and the outer wall includes a downstream wall portion that faces a combustion region. The multiple tubes extend through the chamber to the downstream wall portion, and each tube includes an air inlet into the tube, a fuel inlet including a protrusion extending radially into the tube in a crosswise direction relative to a longitudinal axis of the tube, and an outlet from the tube. | 09-12-2013 |
20130255263 | AIR BLOCKER RING ASSEMBLY WITH RADIAL RETENTION - An air blocker ring assembly includes a proximal end and a distal end, a blocker ring, and a blocker ring support. The blocker ring support includes at least one flange radially overlapping a portion of the blocker. | 10-03-2013 |
20130269350 | TURBINE COMBUSTOR SYSTEM HAVING AERODYNAMIC FEED CAP - Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle. | 10-17-2013 |
20130283802 | COMBUSTOR - A combustor includes an end cap that extends radially across at least a portion of the combustor, wherein the end cap comprises an upstream surface axially separated from a downstream surface. A shroud circumferentially surrounds at least a portion of the end cap, wherein the shroud at least partially defines a fuel plenum between the upstream surface and the downstream surface. A combustion chamber downstream from the end cap defines a longitudinal axis. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap to the combustion chamber. A transition duct circumferentially surrounds at least a portion of the combustion chamber downstream from the end cap and curves tangentially from the longitudinal axis. | 10-31-2013 |
20130283803 | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL INTO A TURBINE ENGINE COMBUSTION CHAMBER - A device for injecting a mixture of air and fuel into a turbine engine combustion chamber, the device including a mechanism for centering a fuel injector, which mechanism is movable radially in a support mechanism fastened to a wall of the chamber, the support mechanism carrying a retaining mechanism for axially retaining the centering mechanism on a side opposite from the chamber wall, the retaining mechanism being fastened in releasable manner to the support mechanism. | 10-31-2013 |
20130298561 | MULTI-TUBE FUEL NOZZLE WITH MIXING FEATURES - A system includes a multi-tube fuel nozzle having an inlet plate and a plurality of tubes adjacent the inlet plate. The inlet plate includes a plurality of apertures, and each aperture includes an inlet feature. Each tube of the plurality of tubes is coupled to an aperture of the plurality of apertures. The multi-tube fuel nozzle includes a differential configuration of inlet features among the plurality of tubes. | 11-14-2013 |
20130298562 | Fuel Injector With Mixing Circuit - A fuel injector having an injector body, a mixing circuit, and at least one injector is provided. The injector body has a plurality of manifolds, an inlet, and an outlet. The manifolds are configured for receiving fuel, and the inlet is configured for receiving air. The mixing circuit is positioned within the injector body. The mixing circuit is configured for receiving fuel from at least one of the manifolds, and air from the inlet to create an air-fuel mixture that exits the outlet. The least one fuel injector is positioned radially outwardly from the mixing circuit. The at least one injector receives fuel from at least one of the plurality of manifolds and injects fuel to the outlet. | 11-14-2013 |
20130318975 | TURBOMACHINE COMBUSTOR NOZZLE INCLUDING A MONOLITHIC NOZZLE COMPONENT AND METHOD OF FORMING THE SAME - A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements. | 12-05-2013 |
20130318976 | TURBOMACHINE COMBUSTOR NOZZLE AND METHOD OF FORMING THE SAME - A turbomachine combustor nozzle includes a first plate member having a first plurality of openings, and a second plate member having a second plurality of openings that are configured and disposed to be in alignment with the first plurality of openings. A plurality of nozzle members extends through corresponding ones of the first plurality of openings and the second plurality of openings. Each of the plurality of nozzle members includes a solid core. | 12-05-2013 |
20130327046 | COMBUSTOR ASSEMBLY HAVING A FUEL PRE-MIXER - A combustor assembly having a fuel pre-mixer including a duct for mixing an airflow and a fuel therein. Also included is a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct. Further included is a planar vane section in communication with the airflow and the fuel to provide a first injection of fuel and a flow conditioning effect on the airflow. Yet further included is a swirler vane section disposed downstream of the planar vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow. | 12-12-2013 |
20130340436 | GAS FUEL TURBINE ENGINE FOR REDUCED OSCILLATIONS - A gas fuel turbine engine may include a gaseous pilot fuel supply, a first main fuel supply, and a second main fuel supply. The first main fuel supply may provide gaseous fuel to a first plurality of fuel injectors, and the second main fuel supply may provide gaseous fuel to a second plurality of fuel injectors. The turbine engine may also include a flow restriction provided in the first main fuel supply. The second main fuel supply may be free of the flow restriction. | 12-26-2013 |
20140013759 | PREMIX BURNER OF THE MULTI-CONE TYPE FOR A GAS TURBINE - The invention relates to a premix burner of the multi-cone type for a gas turbine that includes a plurality of shells which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. The flame front of such a burner is stabilized by providing a virtual common cone with a cone angle, which varies in axial direction. | 01-16-2014 |
20140013760 | PREMIX BURNER OF THE MULTI-CONE TYPE FOR A GAS TURBINE - The invention relates to a premix burner of the multi-cone type for a gas turbine, that includes a plurality of shells, which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. A disadvantageous transition piece between the shells and a downstream mixing tube is avoided by bordering the downstream ends of the shells by intersecting planes, which are defined by intersecting said shells with a virtual coaxial cylinder of a predetermined radius. | 01-16-2014 |
20140013761 | COMBUSTOR ARRANGEMENT, ESPECIALLY FOR A GAS TURBINE - The invention relates to a combustor arrangement that includes a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to said front panel though an elongated mixing zone in an axially moveable fashion by means of a sealed sliding joint. A wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame is achieved by positioning said sealed sliding joint upstream of said mixing zone. | 01-16-2014 |
20140013762 | COMBUSTOR AND GAS TURBINE PROVIDED WITH SAME - A combustor ( | 01-16-2014 |
20140033722 | Fuel-Air Mixer For Use With A Combustor Assembly - A fuel-air mixer for use with a combustor is provided. The fuel-air mixer includes an outer ring, an intermediate hub disposed coaxially within the outer ring such that a first plenum is formed therebetween, and an inner hub disposed coaxially within the intermediate hub such that a second plenum is formed therebetween. A first swirler including a plurality of first swirler vanes is positioned between the outer ring and the intermediate hub, wherein the first swirler is configured to rotate fluid flowing therethrough in a first direction. A second swirler including a plurality of second swirler vanes is positioned between the intermediate hub and the inner hub, wherein the second swirler is configured to rotate fluid flowing therethrough in a second direction. A plurality of fuel injection conduits are also defined within the fuel-air mixer for channeling fuel to the first and second plenums. | 02-06-2014 |
20140033723 | UNKNOWN - The present invention relates to a gas-turbine combustion chamber with mixing air orifices, with a combustion chamber wall, with tiles arranged on the inside of the combustion chamber wall at a certain distance from said combustion chamber wall as well as with mixing air orifices passing through the combustion chamber wall and the tiles, characterized in that the mixing air orifices are formed by chutes which are designed tube-like and pass through the tiles, and that several chutes are formed on a mixing air wall element extending at least around part of the circumference of the combustion chamber. | 02-06-2014 |
20140041389 | NOZZLE, GAS TURBINE COMBUSTOR AND GAS TURBINE - A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage. | 02-13-2014 |
20140041390 | LEAN BURN INJECTORS HAVING MULTIPLE PILOT CIRCUITS - A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit. | 02-13-2014 |
20140083100 | GAS TURBINE ENGINE COMBUSTOR - A swirler assembly for a gas turbine engine includes an outer annular injector which at least partially surrounds an inner injector. | 03-27-2014 |
20140083101 | GAS TURBINE ENGINE PRESWIRLER WITH ANGLED HOLES - A gas turbine engine preswirler ( | 03-27-2014 |
20140083102 | GAS TURBINE COMBUSTOR - An object of the present invention is to provide a combustor having a premixing burner, wherein a conical flame can be formed and the metal temperature at a liner and a burner end face can be reduced. | 03-27-2014 |
20140109582 | SELF-STABILIZED MICROMIXER - A micromixer of a premixer includes a plurality of enhanced minitubes and a plurality of unenhanced minitubes, both of which are arranged to deliver a premixed mixture of fuel and oxidizer to a combustion zone of a combustor. Both the enhanced and unenhanced minitubes are commonly bundled so as to function as a single fuel nozzle of the premixer. Each enhanced minitube includes a turbulence enhancer arranged to disturb a flow of the premixed mixture at the exit of thereof. This intensifies the turbulent jet interaction of the fuel and oxidizer mixture as the mixture suddenly expands from the enhanced minitube, thus providing aerodynamic combustion stabilization. | 04-24-2014 |
20140109583 | BURNER - The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis. | 04-24-2014 |
20140116053 | FUEL INJECTION ASSEMBLIES IN COMBUSTION TURBINE ENGINES - An assembly for use in a fuel injection system within a combustor of a combustion turbine engine is described. The assembly may include: a first port formed through an outer radial wall of the combustor and a second port formed through an inner radial wall. A plenum may be formed about the first port. A tube may be formed that has a first end positioned within the first port and a second end positioned within the second port. At the first end, the tube may be sized smaller than the first port such that two passages are defined therethrough: a first passage defined about an exterior of the tube; and a second passage defined through an interior of the tube. | 05-01-2014 |
20140123650 | MICRO-MIXER NOZZLE - The present application provides a micro-mixer combustion nozzle for mixing a flow of fuel and a flow of air in a gas turbine engine. The micro-mixer combustion nozzle may include a fuel plate with a number of fuel plate apertures and a fuel plate passage in communication with the flow of fuel and an air plate with a number of air plate apertures and an air plate passage in communication with the flow of air. The fuel plate passage and the air plate passage may align to mix in part the flow of fuel and the flow of air. | 05-08-2014 |
20140123651 | SYSTEM FOR PROVIDING FUEL TO A COMBUSTOR ASSEMBLY IN A GAS TURBINE ENGINE - A system for providing fuel to a combustor assembly in a gas turbine engine includes a main fuel valve assembly a plurality of multi-stage combustor valve assemblies. Each multi-stage combustor valve assembly is provided for delivering fuel to a respective combustor of the combustor assembly and includes at least two stage valves, each stage valve in communication with a respective stage within the corresponding combustor. The main fuel valve assembly receives fuel from a source of fuel and selectively delivers the fuel to the plurality of multi-stage combustor valve assemblies. Each stage valve within each multi-stage combustor valve assembly is adjustable to control delivery of fuel to each respective stage. | 05-08-2014 |
20140123652 | GAS TURBINE BURNER - A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor. | 05-08-2014 |
20140137556 | GAS TURBINE COMBUSTOR - A gas turbine combustor includes a combustion cylinder, a premixing tube, and a pressure injection unit. Holes are formed in a peripheral wall of the premixing tube in a tangential direction. An inner wall is provided in the peripheral wall while having a gap therefrom. The compressed air in the gap forms a swirl flow. The compressed air and injected fuel supplied into the inner wall form straight flows each with a predetermined cross-section area in the inner wall under no influence of the swirl flow. They are combusted in the combustion cylinder via a protruding wall. The flame is stably retained at an appropriate position apart from the top portion of the combustion cylinder to improve durability without being excessively heated. This may prevent deterioration in durability of the combustion cylinder by the heat by retaining the flame at the appropriate position in the combustion cylinder. | 05-22-2014 |
20140137557 | GAS TURBINE COMBUSTOR - A gas turbine combustor includes a combustion cylinder and a premixing tube. A protruding wall of the tube has an inner diameter enlarging portion with a chamfer at an open end thereof A swirl flow in the tube is guided outward along the chamfer, so that the cross-section area of a straight flow in the tube is expanded to have a lower flow velocity, and the distance between a flame in the cylinder and the enlarging portion is shortened. When using the fuel with high heat radiation upon combustion, the enlarging portion is replaced with the one having a smaller chamfer. The cross-section area of the straight flow is reduced to increase the flow velocity, and the lift distance becomes longer. Therefore, the damage to the combustion cylinder owing to the intensified heat radiation is prevented. The flame lift position retained in the cylinder is easily set and changed. | 05-22-2014 |
20140144141 | PREMIXER WITH DILUENT FLUID AND FUEL TUBES HAVING CHEVRON OUTLETS - A premixer includes an air tube formed in a burner tube defining a longitudinal axis, and a coaxially disposed fuel tube with a turbulence enhancing chevron outlet. The fuel tube may include an exterior tube and an interior tube with the interior tube, the exterior tube or both having chevron outlets. The chevron outlets may be tapered and notched. | 05-29-2014 |
20140144142 | FUEL NOZZLE FOR USE IN A TURBINE ENGINE AND METHOD OF ASSEMBLY - A fuel nozzle for use in a turbine engine is provided. The fuel nozzle includes at least one premixer tube including a tube wall and a plurality of perforations defined therein and extending through the tube wall. The plurality of perforations are configured to channel a flow of air therethrough. The fuel nozzle also includes a liquid fuel plenum positioned upstream from the premixer tube, and at least one fuel injector coupled in flow communication with the liquid fuel plenum and the at least one premixer tube. The at least one fuel injector is configured to channel a flow of liquid fuel from the liquid fuel plenum into the premixer tube. | 05-29-2014 |
20140144143 | COMBUSTION APPARATUS AND GAS TURBINE ENGINE - A combustion apparatus includes a combustion chamber, a pre-chamber and a first device for mixing a fuel with an oxidant, the first device being located upstream of the pre-chamber. The combustion chamber and the pre-chamber share a common first and second wall spaced to each other building a cavity. The first wall exhibits at least one first opening in the area of the combustion chamber for introducing a coolant into the cavity. Further, the combustion apparatus has a channel for feeding the oxidant to the first device, whereby the channel is formed by a housing element of the combustion apparatus and the common first wall of the combustion chamber and the pre-chamber. The at least one first opening is located in the area of the combustion chamber. The first wall exhibits at least one second opening, located in the area of the pre-chamber, for introducing the coolant into the cavity. | 05-29-2014 |
20140182294 | GAS TURBINE COMBUSTOR - A gas turbine combustor includes a pilot burner, provided at a top portion of a combustion liner having a combustion chamber defined therein, and a main burner of a premixing type disposed adjacent an outer periphery thereof. The pilot burner is provided with an inflow passage, provided in an upstream end portion to allow the compressed air from a radially outer area into a radially inner area, a plurality of fuel supply holes for injecting the fuel into the inflow passage in a direction perpendicular to the flow of the compressed air, a premixing passage for guiding the air-fuel mixture from the inflow passage in an axially downstream direction while the compressed air and the fuel are mixed together, and a plurality of premixed air-fuel mixture injection holes for injecting the premixed air-fuel mixture from the premixing passage into the combustion chamber. | 07-03-2014 |
20140190167 | Ceramic combustor can for a gas turbine engine - A combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween. An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture. | 07-10-2014 |
20140190168 | DUAL FUEL NOZZLE TIP ASSEMBLY - A fuel nozzle for a combustor includes a burner tube and a center nozzle assembly disposed within the burner tube. The center nozzle assembly includes a center body that at least partially defines a cooling air flow passage through the center nozzle assembly. A premix flow passage is defined between the burner tube and the center nozzle assembly. A tip assembly is disposed at a downstream end of the center body. The tip assembly includes an impingement plate, and a cap that is disposed downstream from the impingement plate. The impingement plate and the cap at least partially define a cooling plenum therebetween. An insert passage extends through the impingement plate and a cooling flow outlet extends through the cap. A plurality of cooling ports extends through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum. | 07-10-2014 |
20140216038 | Variable Volume Combustor with Cantilevered Support Structure - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within an end cover, a common fuel tube extending through the end cover and in communication with the micro-mixer fuel nozzles, a linear actuator to maneuver the common fuel tube and the micro-mixer fuel nozzles, and a sealing support structure positioned between the end cover and the common fuel tube. | 08-07-2014 |
20140216039 | Variable Volume Combustor with Aerodynamic Fuel Flanges for Nozzle Mounting - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts. | 08-07-2014 |
20140216040 | Variable Volume Combustor with a Conical Liner Support - The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a conical liner support supporting the liner. | 08-07-2014 |
20140216041 | Variable Volume Combustor with Center Hub Fuel Staging - The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle. | 08-07-2014 |
20140238025 | FUEL/AIR MIXING SYSTEM FOR FUEL NOZZLE - A system includes a fuel nozzle. The fuel nozzle includes a central hub with a first annular passage extending along a longitudinal axis of the fuel nozzle. A flow conditioner is disposed along the first annular passage. The flow conditioner includes at least one of a straightening vane, a mesh screen, or a multi-passage body having multiple passages generally parallel with the longitudinal axis. An outer shroud is disposed about the central hub to define a second annular passage extending along the longitudinal axis of the fuel nozzle. | 08-28-2014 |
20140250892 | LEAN FUEL INTAKE GAS TURBINE - A lean fuel intake gas turbine which uses, as a working gas, a mixed gas having a concentration equal to or lower than a flammability limiting concentration and obtained by mixing two types of fuel gases having different fuel concentrations, includes a first mixer configured to mix a second fuel gas having a higher fuel concentration with a first fuel gas having a lower fuel concentration, of the two types of the fuel gases having different fuel concentrations, to generate a first stage mixed gas and a second mixer configured to further mix the second fuel gas with the first stage mixed gas to generate a second stage mixed gas which is the working gas. | 09-11-2014 |
20140260266 | COMBUSTOR FOR GAS TURBINE ENGINE - A gas turbine engine comprises an annular combustor chamber formed between an inner liner and an outer liner. An annular upstream zone is adapted to receive fuel and air from an annular nozzle. An annular mixing zone is located downstream of the upstream zone. The mixing zone has a reduced radial height relative a downstream combustion zone of the combustion chamber, the mixing zone defined by straight wall sections. | 09-18-2014 |
20140260267 | COMBUSTOR END COVER WITH FUEL PLENUMS - A system includes a system having an end cover of a combustor for a gas turbine. The end cover has at least one fuel plenum coupled to a plurality of fuel injectors for a multi-tube fuel nozzle having a plurality of fuel-air mixing tubes, each tube having one of the fuel injectors. At least one fuel plenum is configured to provide fuel to each of the fuel injectors. | 09-18-2014 |
20140260268 | MICROMIXING CAP ASSEMBLY - A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow, a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector and is individually removable from the combustor cap assembly, an air distributor disposed within the interior volume and configured to distribute the air flow received by the interior volume to each of the plurality of mixing tubes, and a combustor cap removably coupled to the support structure. | 09-18-2014 |
20140260269 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine engine that includes: a combustor coupled to a turbine and a downstream injection system that includes two injection stages, a first stage and a second stage, positioned within an interior flowpath, wherein the first stage comprises an axial position that is aft of the primary air and fuel injection system and the second stage comprising an axial position that is aft of the first stage. Each of the first stage and the second stage include a plurality of circumferentially spaced injectors, each injector of which is configured to inject air and fuel into a flow through the interior flowpath. The first stage and the second stage have a configuration that limits a fuel injected at the second stage to less than 50% of a fuel injected at the first stage. | 09-18-2014 |
20140260270 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine engine that includes: an interior flowpath defined through a combustor and a turbine; an aft frame forming an interface between the combustor the turbine, the aft frame comprising a rigid structural member that circumscribes the interior flowpath, wherein the aft frame includes an inner wall that defines an outboard boundary of the interior flowpath; a circumferentially extending fuel plenum formed through the aft frame; and outlet ports formed through the inner wall of the aft frame. The outlet ports may be configured to connect the fuel plenum to the interior flowpath. | 09-18-2014 |
20140260271 | System Having a Multi-Tube Fuel Nozzle - A system including a plurality of multi-tube fuel nozzles each having a plurality of tubes extending in an axial direction, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, a fuel nozzle housing including a first outer wall extending circumferentially about a central axis, wherein the plurality of multi-tube fuel nozzles are disposed in the fuel nozzle housing, an inlet flow conditioner removably coupled to a first end portion of the first outer wall, wherein the inlet flow conditioner includes a plurality of air openings, and an aft plate assembly removably coupled to a second end portion of the first outer wall, wherein the aft plate assembly includes an aft plate having a plurality of tube apertures, and the plurality of tubes extend to the plurality of tube apertures. | 09-18-2014 |
20140298814 | CATALYTIC COMBUSTION AIR HEATING SYSTEM - A system for pre-heating a working fluid within a combustor includes a compressor for providing the working fluid to the combustor. An outer casing is disposed downstream from the compressor. The outer casing at least partially defines a high pressure plenum that at least partially surrounds the combustor. A combustion chamber is defined within the combustor downstream from the high pressure plenum. A catalytic combustor is disposed within the high pressure plenum upstream from the combustion chamber so as to provide thermal energy to the working fluid upstream from the combustion chamber. | 10-09-2014 |
20140311150 | FUEL NOZZLE FOR A PRE-MIX COMBUSTOR OF A GAS TURBINE ENGINE - A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage. The first swirler vane provides a first wake region within the flow segment. The second swirler vane provides a second wake region within the flow segment. A fuel injection peg is disposed downstream from the first swirler vane and the second swirler vane. The fuel injection peg is positioned within the flow segment between the first wake region and the second wake region. | 10-23-2014 |
20140311151 | GAS TURBINE COMBUSTOR - Provided is a gas turbine combustor having improved maintainability obtained by facilitating the mounting and removal of a base plate for supporting main burners and a pilot burner. A gas turbine combustor is provided with: a pilot burner disposed at the center of a combustor inner tube; main burners provided on the outside of the pilot burner in the radial direction so as to be arranged in the circumferential direction of the inner peripheral surface of the combustor inner tube; a circular disc-shaped base plate disposed within the combustor inner tube and supporting both the pilot burner and the main burners; and an engagement section protruding from the inner peripheral surface toward the inside thereof in the radial direction and engaging with the base plate. The base plate, and the engagement section or the inner peripheral surfaces are affixed by bolts. | 10-23-2014 |
20140318135 | CAN COMBUSTOR FOR A CAN-ANNULAR COMBUSTOR ARRANGEMENT IN A GAS TURBINE - The invention relates to a can-combustor for a can-annular combustor arrangement in a gas turbine. The can combustor includes an essentially cylindrical casing with an axially upstream front panel and an axially downstream outlet end. The can combustor further includes a number of premixed burners, extending in an upstream direction from said front panel and having a burner exit, supported by this front panel, for supplying a fuel/air mixture into a combustion zone inside the casing. Up to four premixed burners are attached to the front panel in a substantially annular array. Each burner has a conical swirl generator and a mixing tube to induce a swirl flow of said fuel/air mixture. | 10-30-2014 |
20140331675 | PIVOTING SWIRLER INLET VALVE PLATE - A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The blocker ring includes a blocking surface perpendicular to an axis of the blocker ring formed from at least a portion of an annulus. The blocker ring also includes a flow surface, an inner circumferential surface of the toroidal shape. The pivot sleeve includes a sleeve portion extending adjacent the blocker ring. The sleeve portion includes a rotation transmission mechanism. | 11-13-2014 |
20140338336 | GAS TURBINE ENGINE COMBUSTOR WITH INTEGRATED COMBUSTOR VANE - A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber. | 11-20-2014 |
20140338337 | INJECTORS FOR MULTIPOINT INJECTION - An injector for a multipoint combustor system includes an inner air swirler which defines an interior flow passage and a plurality of swirler inlet ports in an upstream portion thereof. The inlet ports are configured and adapted to impart swirl on flow in the interior flow passage. An outer air cap is mounted outboard of the inner swirler. A fuel passage is defined between the inner air swirler and the outer air cap, and includes a discharge outlet between downstream portions of the inner air swirler and the outer air cap for issuing fuel for combustion. The outer air cap defines an outer air circuit configured for substantially unswirled injection of compressor discharge air outboard of the interior flow passage. | 11-20-2014 |
20140338338 | SYSTEM AND METHOD FOR TUBE LEVEL AIR FLOW CONDITIONING - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple mixing tubes. Each mixing tube includes an annular wall disposed about a central passage and an air inlet region configured to be disposed about a fuel injector extending into the central passage. The central passage extends from an upstream end to a downstream end of the annular wall relative to a direction of flow through the central passage. The air inlet region includes an air entry surface of the annular wall that gradually decreases in diameter in the direction of flow. | 11-20-2014 |
20140338339 | SYSTEM AND METHOD HAVING MULTI-TUBE FUEL NOZZLE WITH MULTIPLE FUEL INJECTORS - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube. | 11-20-2014 |
20140345286 | GAS TURBINE ENGINES WITH FUEL INJECTOR ASSEMBLIES - In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem defining a fuel path for fuel and a flow guide coupled to and extending along the stem. The flow guide receives an air flow. The assembly further includes a swirler apparatus coupled to the stem and configured to receive the fuel. The swirler apparatus is further coupled to the flow guide and configured to receive the air flow. The swirler apparatus is configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly. | 11-27-2014 |
20140352312 | Injector for introducing a fuel-air mixture into a combustion chamber - An injector ( | 12-04-2014 |
20140373548 | COMBUSTION CHAMBER OF A COMBUSTOR FOR A GAS TURBINE - A combustion chamber of a combustor for a gas turbine is provided. A combustion chamber includes a plurality of segments arranged annularly about an axis of the combustion chamber, each segment comprising a radial inner wall portion and a radial outer wall portion, a first section comprising an opening for the installation of a burner, and a second section at which at least one airfoil extends between the radial inner wall portion and radial outer wall portion of the segment. | 12-25-2014 |
20150013339 | MIXING ARRANGEMENT FOR MIXING A FUEL WITH A STREAM OF OXYGEN CONTAINING GAS - The invention relates to a mixing arrangement for mixing a fuel with a stream of oxygen containing gas flowing along an axis in an axial channel, especially in the second combustor of a gas turbine with sequential combustion. The mixing is improved and the mixing length reduced by said mixing arrangement comprising an injector with at least one injector ring, which is passed by said stream of gas inside and outside. | 01-15-2015 |
20150059346 | DEVICE FOR INJECTING AIR AND FUEL INTO A COMBUSTION CHAMBER OF A TURBINE ENGINE - A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath. | 03-05-2015 |
20150121882 | MIXER ASSEMBLY FOR A GAS TURBINE ENGINE - A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler. | 05-07-2015 |
20150135716 | ANTI-COKING LIQUID CARTRIDGE - A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels. | 05-21-2015 |
20150135717 | Gas Turbine Combustor - A gas turbine combustor including a cluster-type burner is adapted to stabilize a combustion state by supplying a desired flow rate of combustion air to inner circumferential and outer circumferential fuel nozzle regions. A burner section of the combustor includes a plurality of fuel nozzles | 05-21-2015 |
20150300648 | GAS TURBINE COMBUSTOR AND GAS TURBINE - A gas turbine combustor forms a combustion region R | 10-22-2015 |
20150354823 | Gas Turbine Combustor - A gas turbine combustor is provided that can stably burn two kinds of gas fuels having different heating values by means of the same burner. In the gas turbine combustor that includes a combustion chamber for mixing fuel and air for combustion and a burner, disposed upstream of the combustion chamber, for jetting fuel and air into the combustion chamber and holding flames, the burner has a first swirler including a plurality of fuel holes and of air holes circumferentially alternately and a second swirler including a plurality of holes through which to jet fuel or air, the second swirler is disposed on the outer circumference of the first swirler, and each of the holes of the second swirler is greater in width than each of the air holes of the first swirler. | 12-10-2015 |
20150354824 | Variable Swirl Fuel Nozzle - A fuel injector providing a flow of fuel having a variable swirl and/or variable effective area is disclosed. The fuel injector may have a nozzle defining a mixing chamber having an outlet proximate a centerline of the mixing chamber, a first fuel line in fluid communication with the mixing chamber and a second fuel line in fluid communication with the mixing chamber. The first fuel line may terminate in a tangential fuel inlet positioned tangential to the centerline of the nozzle, while the second fuel line may terminate in a radial fuel inlet positioned radial to the centerline of the nozzle. | 12-10-2015 |
20150361895 | Atomizer, Combustion Device Including Atomizer, and Gas Turbine Plant - An atomizer of the invention includes a mixing chamber, spray fluid flow passages supplying a spray fluid to the mixing chamber, a spray medium flow passage supplying a spray medium to the mixing chamber, outlet holes spraying a fluid mixture of the spray fluid and the spray medium, and fluid mixture flow passages connecting the mixing chamber and the outlet holes to each other. The fluid mixture flowing through each of the fluid mixture flow passages joins with each other at a joining section and is sprayed from the outlet hole. The mixing chamber includes a middle ejection hole spraying the spray fluid to the mixing chamber. The middle ejection hole is arranged at a joining section of the spray fluid flow passages. The spray fluid flowing through the spray fluid flow passages joins with each other at the joining section and is sprayed from the middle ejection hole. | 12-17-2015 |
20150377489 | INJECTION SYSTEM FOR A TURBINE ENGINE COMBUSTION CHAMBER CONFIGURED FOR DIRECT INJECTION OF TWO COAXIAL FUEL FLOWS - In known types of injection systems for a turbine engine combustion chamber, the secondary fuel flow strikes the venturi before entering into the combustor. A new injection system is disclosed to overcome this problem, comprising a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. This first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius ψ of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector. | 12-31-2015 |
20160003478 | DILUTION HOLE ASSEMBLY - A dilution hole assembly that may be of a combustor has a first wall that defines a hole that may communicate through a liner and outer shell of the combustor for flowing dilution air from an air plenum located outward of the shell and into a combustion chamber defined by and located inward of the liner. The assembly has an outer wall that may be engaged to the shell and liner, and which defines the hole. An inner wall of the assembly may be in the hole such that an annular portion of the hole is defined between the inner and outer walls. A plurality of vanes may be in the annular portion and spaced from one-another for swirling air that flows through the annular portion. The walls may be generally conical in shape and/or radially sloped such that air flowing through the annular portion and air flowing at least through the inner portion impinge upon one-another adding to the air turbulence created by the swirling action of the vanes and thus enhancing efficient combustion and temperature profiling within the combustion chamber. | 01-07-2016 |
20160003481 | COMBUSTOR AND GAS TURBINE - A combustor includes a first tube which supplies fuel and air from an opening formed in a distal end thereof, and a second tube which is configured such that flames are formed on an inner circumferential side thereof by the fuel and the air and the distal end of the first tube is inserted into an inner circumferential side of a proximal end thereof. The first tube includes a first tube main body and a ring part forming the distal end of the first tube. The ring part has a main body of a tubular shape and a plurality of protrusions that are integrally formed with the main body on an outer circumferential surface of the main body and protrude radially outward. When viewed in an axial direction, the outer circumferential surface of the main body has a polygonal cross-sectional shape within a range within which the protrusions are formed. | 01-07-2016 |
20160010856 | AXIAL SWIRLER | 01-14-2016 |
20160017805 | IGNITER TIP WITH COOLING PASSAGE - A combustor cap for a combustor chamber of a combustion system is provided. The combustor cap includes a plate member including: a plurality of openings for accommodating a plurality of fuel nozzles of the combustion system; a cooling passage extending through a plane of the plate member; an entrance opening to the cooling passage; and an exit opening from the cooling passage to a side of the plate member opposite to the combustion chamber. | 01-21-2016 |
20160033132 | FUEL INJECTOR TO FACILITATE REDUCED NOX EMISSIONS IN A COMBUSTOR SYSTEM - A fuel injector to reduce NO | 02-04-2016 |
20160033133 | COMBUSTOR NOZZLES IN GAS TURBINE ENGINES - A micro-mixer nozzle for use in a combustor of a combustion turbine engine, the micro-mixer nozzle including: a fuel plenum defined by a shroud wall connecting a periphery of a forward tube sheet to a periphery of an aft tubesheet; a plurality of mixing tubes extending across the fuel plenum for mixing a supply of compressed air and fuel, each of the mixing tubes forming a passageway between an inlet formed through the forward tubesheet and an outlet formed through the aft tubesheet; and a wall mixing tube formed in the shroud wall. | 02-04-2016 |
20160033136 | GAS TURBINE COMBUSTOR - A gas turbine combustor comprising a burner including:
| 02-04-2016 |
20160040883 | Gas Turbine Combustor - A gas turbine combustor of the present invention includes a cylindrical combustor liner, a cylindrical combustion chamber inside the combustor liner, and a burner that includes a plurality of fuel nozzles for injecting the gas fuel into the combustion chamber and an air hole plate with a plurality of air holes for guiding the compressed air into the combustion chamber. The air hole plate joins the combustor liner and is disposed between the fuel nozzles and the combustion chamber. The junction between the air hole plate and the combustor liner is provided with an inclined component which covers the junction and has a connecting surface connecting the air hole plate and the combustor liner. | 02-11-2016 |
20160061452 | CORRUGATED CYCLONE MIXER ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS AND IMPROVE OPERABILITY IN A COMBUSTOR SYSTEM - A corrugated cyclone mixer for use in a fuel injection assembly of a turbine engine. The corrugated cyclone mixer generally includes an annular housing including a flange portion and a lip portion configured downstream of the flange portion. The mixer further including a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer. The swirler is configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow. The lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end. The plurality of corrugations are configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer. Additionally disclosed is a fuel injection assembly and a turbine assembly including the corrugated cyclone mixer. | 03-03-2016 |
20160061453 | COMBUSTOR DYNAMICS MITIGATION - A combustor includes a plurality of bundled tube fuel nozzles which are annularly arranged around a common axial centerline. The plurality of bundled tube fuel nozzles comprise a first bundled tube fuel nozzle and a second bundled tube fuel nozzle. The first bundled tube fuel nozzle includes a first fuel plenum and a plurality of premix tubes which extend axially therethrough. The second bundled tube fuel nozzle includes a second fuel plenum and a plurality of premix tubes which extend axially therethrough. The first fuel plenum is axially offset at a predefined axial distance from the second fuel plenum so as to mitigate combustion tones within the combustor. In one embodiment, premix tube fuel ports disposed within the first and/or second fuel plenums may be axially offset with respect to each other within the corresponding fuel plenums at a predefined axial distance to mitigate combustion tones within the combustor. | 03-03-2016 |
20160091207 | COMBUSTOR AND GAS TURBINE HAVING THE SAME - A combustor is equipped with a burner case, and a base plate spreading from a downstream end of the burner case in a radial direction. The base plate defines a purging air space at an upstream side of the base plate. The combustor is formed with a purging air flow passage that injects purging air in the purging air space to a downstream side relative to the base plate. An outflow opening of the purging air flow passage is formed within an opening formation range. The opening formation range is made up of a range from the downstream end of the burner case to a plate thickness dimension of the base plate toward the upstream side, and a range from an inner circumferential surface of the burner case to the plate thickness dimension of the base plate in the radial direction. | 03-31-2016 |
20160146459 | PREMIX FUEL NOZZLE ASSEMBLY - A premix fuel nozzle assembly includes a center body including a sleeve having an inner surface and a pilot premix fuel nozzle assembly that extends axially through the center body within the sleeve and defines a pilot air passage within the center body. The pilot premix fuel nozzle assembly includes a premix tip having a plurality of premix tubes that define premix passages in fluid communication with the pilot air passage. At least one of the premix tubes includes a fuel port. The premix fuel nozzle assembly further includes a pilot fuel flow path that is defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve and a fuel plenum that is at least partially defined between the sleeve inner surface and an outer surface of the premix tip. The fuel ports provide for fluid communication between the fuel plenum and the premix passages. | 05-26-2016 |
20160146460 | PREMIX FUEL NOZZLE ASSEMBLY - A premix fuel nozzle assembly includes a center body, a pilot premix fuel nozzle assembly that extends axially through the center body and that includes a premix tip having a plurality of premix tubes that each defines a premix passage and a fuel port. The premix passage of each premix tube is in fluid communication with the pilot air passage. The premix fuel nozzle assembly further includes a purge air cartridge assembly that extends axially within the pilot air passage. The purge air cartridge assembly includes a feed tube portion and a tip portion that define a purge air passage within the pilot air passage. The tip portion comprises an aft wall that extends at least partially through an opening defined by the premix tip. The aft wall includes a single axially extending orifice that is in fluid communication with the purge air passage. | 05-26-2016 |
20160146466 | LOBE LANCE FOR A GAS TURBINE COMBUSTOR - A lobe lance is disclosed for a gas turbine combustor which includes a plurality of N (N≧4) lobe fingers, each configured as a streamlined body with two lateral surfaces. A plurality of nozzles for injecting a gaseous and/or liquid fuel mixed with air are provided whereby lobes running between the nozzles are provided for improving the mixing quality and reducing pressure loss in said combustor. The lobes of each lobe finger have one of two opposite orientations with respect to said flow direction, and the lobes of all lobe fingers follow a predetermined pattern of orientation across the lobe fingers at least one pair of neighboring lobe fingers has the same lobe orientation resulting in a grouped lobe arrangement ( . . . LL . . . or . . . RR . . . ) such that at least two of the vortices generated by the lobe shape downstream of the lobe fingers combine. | 05-26-2016 |
20160146469 | BUNDLED TUBE FUEL NOZZLE - A bundled tube fuel nozzle includes a fuel distribution body. The fuel distribution body includes a substantially flat aft wall having an inner surface axially spaced from an outer surface, a fuel stem collar axially spaced from the inner surface of the aft wall and a contoured forward wall that extends between the fuel stem collar and the aft wall. The contoured forward wall and the aft wall define a fuel plenum within the fuel distribution body. The bundled tube fuel nozzle further includes a plurality of injector tubes that are in fluid communication with the fuel plenum. Each injector tube extends from the contoured forward wall to the aft wall within the fuel distribution body and defines a premix passage through the contoured forward, the fuel plenum and the aft wall. | 05-26-2016 |
20160146470 | BURNER OF A GAS TURBINE - The burner of a gas turbine has a duct, a vortex generator extending in the duct and including a leading edge and a trailing edge. The trailing edge has a first order lobed shape. The first order lobed shape is defined by a second order lobed shape. Preferably a nozzle for fuel injection is connected to the vortex generator and the second order lobed shape is only provided at the nozzles. | 05-26-2016 |
20160153662 | ANNULAR DEFLECTION WALL FOR A TURBOMACHINE COMBUSTION CHAMBER INJECTION SYSTEM PROVIDING A WIDE FUEL ATOMIZATION ZONE | 06-02-2016 |
20160161125 | SEQUENTIAL BURNER FOR AN AXIAL GAS TURBINE - A sequential burner for an axial gas turbine comprises: a burner body, which is designed as an axially extending hot gas channel and further comprises a fuel injection device, which extends into said burner body perpendicular to the axial direction. The manufacturing of the burner body is simplified and the fuel injection is stabilized by designing said fuel injection device as a mechanically stiff component, and fixing said fuel injection device to said burner body in order to keep it aligned with said burner body and to stiffen said burner body against creep. | 06-09-2016 |
20160169160 | FUEL INJECTION DEVICE FOR GAS TURBINE | 06-16-2016 |
20160169524 | INJECTION SYSTEMS FOR FUEL AND GAS | 06-16-2016 |
20160186663 | PILOT NOZZLE IN GAS TURBINE COMBUSTOR - A fuel nozzle for a gas turbine engine that includes: an elongated centerbody; an elongated peripheral wall formed about the centerbody so to define a primary flow annulus therebetween; a primary fuel supply and a primary air supply in the primary flow annulus; and a pilot nozzle. The pilot nozzle may be formed in the centerbody and include: axially elongated mixing tubes defined within a centerbody wall; a fuel port positioned on the mixing tubes for connecting each to a secondary fuel supply; and a secondary air supply configured so to fluidly communicate with an inlet of each of the mixing tubes. A plurality of the mixing tubes may be formed as canted mixing tubes that are configured for inducing a swirling downstream flow, while a plurality of the mixing tubes may be axial mixing tubes. | 06-30-2016 |
20160186671 | SYSTEM AND METHOD FOR PURGING FUEL FROM TURBOMACHINE - A system includes a fuel premixer configured to distribute a fuel to a combustor and a purge system configured to purge the fuel from the fuel premixer. The purge system includes a discharge line configured to receive a flow of a purge mixture from the fuel premixer. The purge system includes an orifice coupled to the discharge line and an eductor having an interior, an opening, and an outlet. The orifice is configured to constrict the flow of the purge mixture. The interior is fluidly coupled to the orifice, to the opening, and to the outlet. The purge mixture is configured to flow through the interior from the orifice to the outlet, the flow of the purge mixture through the orifice is configured to draw coolant into interior of the eductor through the opening, and the coolant drawn through the opening is configured to mix with the purge mixture. | 06-30-2016 |
20160195274 | AIRBLAST FUEL INJECTOR | 07-07-2016 |
20160201918 | SMALL ARRAYED SWIRLER SYSTEM FOR REDUCED EMISSIONS AND NOISE | 07-14-2016 |
20160252253 | ENHANCED MIXING TUBE ELEMENTS | 09-01-2016 |
20160377294 | FUEL NOZZLE FOR GAS TURBINE COMBUSTOR - A fuel nozzle for gas turbine combustor of the present invention includes a diffusion combustion burner including a diffusion fuel nozzle, a premixing combustion burner including a premixing fuel nozzle, an end flange to which the diffusion combustion burner and the premixing combustion burner are mechanically joined, and a diffusion combustion burner support which fixes the diffusion combustion burner to the end flange and is mounted around the premixing fuel nozzle in a manner to cover a root portion of the premixing fuel nozzle, the root portion being a junction between the premixing fuel nozzle and the end flange. An outside diameter of the premixing fuel nozzle longitudinally varies in a manner to progressively increase toward the junction. A maximum diameter of the root portion of the premixing fuel nozzle is greater than an inside diameter of a hole formed in the diffusion combustion burner support. | 12-29-2016 |