Patent application number | Description | Published |
20090249789 | BURNER TUBE PREMIXER AND METHOD FOR MIXING AIR AND GAS IN A GAS TURBINE ENGINE - A burner for use in a gas turbine engine includes a burner tube having an inlet end and an outlet end; a plurality of slots formed in the burner tube and configured to introduce air flows tangentially into the burner tube and impart swirl to the air flows; a plurality of fuel passages extending axially along the burner tube; and a plurality of fuel injection holes provided to each fuel passage. At least one of the fuel injection holes of each fuel passage is configured to inject a fuel flow tangentially into the burner tube between air flows of adjacent slots to form a fuel and air co-flow. A method of mixing air and fuel in a burner of a gas turbine is provided. The burner includes a burner tube including a plurality of slots formed in the burner tube. The method includes introducing air flows tangentially into the burner tube through the slots and imparting swirl to the air flows; and injecting fuel between air flows of adjacent slots to form fuel and air co-flows. This eliminates jet cross flow, which tends to cause flame holding. The tangentially entered fuel and air co-flow layers then flow down axially with quick mixing and dump to a combustor for a stable premixed combustion. | 10-08-2009 |
20100162711 | DLN DUAL FUEL PRIMARY NOZZLE - The primary nozzles of a Dry Low NOx (DLN) combustor are configured to alternatively burn a first gas fuel or a second gas fuel, where the two gas fuels may have widely disparate energy content. Natural gas may be the first gas fuel and syngas may be the second gas fuel. An inner fuel circuit and an outer fuel circuit are provided to allow effective control of fuel/air mixing profiles, dynamics, primary pre-ignition and emission control by changing the fuel split between the two fuel circuits. The inner fuel circuit may be run in a diffusion combustion mode on many gas fuels. | 07-01-2010 |
20100269507 | RADIAL LEAN DIRECT INJECTION BURNER - A burner for use in a gas turbine engine includes a burner tube having an inlet end and an outlet end; a plurality of air passages extending axially in the burner tube configured to convey air flows from the inlet end to the outlet end; a plurality of fuel passages extending axially along the burner tube and spaced around the plurality of air passage configured to convey fuel from the inlet end to the outlet end; and a radial air swirler provided at the outlet end configured to direct the air flows radially toward the outlet end and impart swirl to the air flows. The radial air swirler includes a plurality of vanes to direct and swirl the air flows and an end plate. The end plate includes a plurality of fuel injection holes to inject the fuel radially into the swirling air flows. A method of mixing air and fuel in a burner of a gas turbine is also provided. The burner includes a burner tube including an inlet end, an outlet end, a plurality of axial air passages, and a plurality of axial fuel passages. The method includes introducing an air flow into the air passages at the inlet end; introducing a fuel into fuel passages; swirling the air flow at the outlet end; and radially injecting the fuel into the swirling air flow. | 10-28-2010 |
20100281876 | FUEL BLANKETING BY INERT GAS OR LESS REACTIVE FUEL LAYER TO PREVENT FLAME HOLDING IN PREMIXERS - A premixer for a gas turbine combustor includes a first passage configured to inject a highly reactive fuel; and a second passage configured to inject an inert gas or a less reactive fuel or a mixture of both. The second passage is configured to form a layer of the inert gas or less reactive fuel or the mixture of both that blankets a layer of the highly reactive fuel. Another premixer includes a plurality of nozzles, each nozzle including a pair of concentric tubes, the pair of concentric tubes including a first tube configured to inject a highly reactive fuel and a second tube surrounding the first tube and configured to dispense an inert gas or a less reactive fuel or a mixture of both that blankets the highly reactive fuel. | 11-11-2010 |
20110067379 | DUAL FUEL COMBUSTOR NOZZLE FOR A TURBOMACHINE - A dual fuel combustor nozzle includes a body member including a first end portion that extends to a second end portion through an intermediate portion. The intermediate portion includes an outer wall portion and an inner wall portion with the inner wall portion defining a first fuel plenum. The dual fuel nozzle also includes an inner nozzle member arranged within the first fuel plenum. The inner nozzle member includes a first end section that extends to a second end section through an intermediate section. The intermediate section defines a second fuel plenum. The second end section being spaced from the second end portion of the body member so as to define a pre-emergence zone. | 03-24-2011 |
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 |
20110083442 | APPARATUS AND METHOD FOR COOLING NOZZLES - A nozzle includes a nozzle body and a cavity defined at least in part by the nozzle body. A plenum extends through the nozzle body into the cavity. At least one passage through the plenum provides fluid communication between the plenum and the cavity. Orifices through the nozzle body and circumferentially spaced around the nozzle body provide fluid communication through the nozzle body. A method for cooling a face of a nozzle having a nozzle body that defines a cavity includes flowing a fuel through the cavity and inserting a plenum through the nozzle body into the cavity. The method further includes flowing a fluid through the plenum so that the fluid impinges on the face of the nozzle to remove heat. | 04-14-2011 |
20110094234 | FUEL FLEXIBLE COMBUSTOR SYSTEMS AND METHODS - The present application provides a combustor. The combustor may include a number of nozzles, a first fuel source with a low reactivity fuel therein, a second fuel source with a high reactivity fuel therein, and a primary valve for varying the flow of the low reactivity fuel and the high reactivity fuel delivered to the nozzles. | 04-28-2011 |
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 |
20110162343 | SYSTEMS AND METHODS FOR CONTROLLING FUEL FLOW WITHIN A MACHINE - Systems and methods for controlling fuel flow within a machine are provided. A plurality of fuel types provided to the machine and a plurality of fuel circuits associated with the machine may be identified, each of the plurality of fuel circuits adapted to be provided with one or more of the plurality of fuel types. A fuel flow parameter for calculating fuel flow may be identified, and a respective fuel flow for each of the one or more fuel types provided to each of the plurality of fuel circuits may be calculated based at least in part on the identified fuel flow parameter. Based at least in part on the calculation of the respective fuel flows, operation of one or more fuel flow control devices providing fuel to the plurality of fuel circuits may be controlled. | 07-07-2011 |
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 |
20110225974 | Multiple Zone Pilot For Low Emission Combustion System - A method of operating a combustor includes delivering a primary fuel flow through a plurality of primary fuel nozzles toward a primary combustion zone and combusting the primary fuel flow in the primary combustion zone. A secondary fuel flow is delivered through a secondary fuel nozzle toward a secondary combustion zone and combusted therein. The secondary fuel is located such that the plurality of primary fuel nozzles are arrayed around the secondary fuel nozzle. An outer swirler is located between the plurality of primary fuel nozzles and the secondary fuel nozzle and includes a plurality of outer swirler channels extending therethrough. A flow of swirler fuel is delivered through the plurality of outer swirler channels into the combustor substantially between the primary combustion zone and the secondary combustion zone to stabilize combustion in the primary combustion zone and/or the secondary combustion zone. | 09-22-2011 |
20110240769 | VARIABLE AREA FUEL NOZZLE - A nozzle is provided and includes a circuit by which fuel is delivered to a nozzle part and a valve, interposed between the circuit and the nozzle part and upon which the fuel impinges, an opening and closing of the valve being passively responsive to a fuel pressure in the circuit such that the valve thereby modulates a size of an area through which a corresponding quantity of the fuel flows from the circuit to the nozzle part. | 10-06-2011 |
20110243805 | FLUID COOLED REFORMER AND METHOD FOR COOLING A REFORMER - The present subject matter discloses a fluid cooled reformer for gas turbine systems and a method for cooling both a fuel reformer and a heated reformate stream produced by such fuel reformer. The fluid cooled reformer may include a pressure vessel and a reactor assembly disposed within the pressure vessel. The reactor assembly may include a reactor and may be configured to receive and reform an oxygen/fuel mixture to produce a heated reformate stream. Additionally, the fluid cooled reformer may include an inlet configured to direct a fluid stream into the pressure vessel. At least a portion of the fluid stream may be used to cool the reactor assembly. A reformate cooling section may be disposed downstream of the reactor of the reactor assembly and may be configured to cool the heated reformate stream. | 10-06-2011 |
20110289929 | TURBOMACHINE FUEL NOZZLE - A turbomachine includes a compressor, a turbine operatively coupled to the compressor, and a combustor fluidly linking the compressor and the turbine. The combustor includes at least one fuel nozzle. The at least one fuel nozzle includes a flow passage including a body having first end that extends to a second end through at least one flow channel having a flow area. A fuel inlet is provided at the first end of the body. The fuel inlet is configured to receive at least one fuel. A fuel outlet is provided at the second end of the body. A control flow passage is fluidly connected to the body between the first and second ends. The control flow passage is configured and disposed to deliver a control flow into the fuel nozzle. The control flow establishes a selectively variable effective flow area of the flow passage. | 12-01-2011 |
20120011854 | FLAME TOLERANT SECONDARY FUEL NOZZLE - A combustor for a gas turbine engine includes a plurality of primary nozzles configured to diffuse or premix fuel into an air flow through the combustor; and a secondary nozzle configured to premix fuel with the air flow. Each premixing nozzle includes a center body, at least one vane, a burner tube provided around the center body, at least two cooling passages, a fuel cooling passage to cool surfaces of the center body and the at least one vane, and an air cooling passage to cool a wall of the burner tube. The cooling passages prevent the walls of the center body, the vane(s), and the burner tube from overheating during flame holding events. | 01-19-2012 |
20120085834 | Flame Tolerant Primary Nozzle Design - A fuel nozzle includes a nozzle cavity with a side wall defining an annular cavity, and swirler vanes arranged circumferentially around an outer surface of the nozzle cavity. A plurality of ports are formed in the side wall and are circumferentially spaced around the nozzle cavity. The ports provide fluid communication through the side wall. The plurality of ports are positioned and/or oriented such that fuel jets communicated through the side wall are communicated downstream of the swirler vanes. | 04-12-2012 |
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 |
20120167544 | Combustor with Fuel Staggering for Flame Holding Mitigation - The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit. | 07-05-2012 |
20120180497 | FUEL REFORMER SYSTEM FOR A TURBOMACHINE SYSTEM - A turbomachine system includes a compressor portion having a compressor inlet and a compressor outlet, a turbine portion operatively connected to the compressor portion, a combustor having a combustor inlet fluidly connected to the compressor outlet and a combustor outlet fluidly connected to the turbine portion; and a reformer having a reformer inlet fluidly connected to the compressor outlet and a reformer outlet fluidly connected to the combustor inlet. The reformer partially combusts air from the compressor portion and a fuel to form a hydrogen-rich syngas. | 07-19-2012 |
20120186266 | REFORMED MULTI-FUEL PREMIXED LOW EMISSION COMBUSTOR AND RELATED METHOD - A reformer for use in a gas turbine engine specially configured to treat a supplemental fuel feed to the combustor that includes a reformer core containing a catalyst composition and an inlet flow channel for transporting the reformer fuel mixture, air and steam (either saturated or superheated) into a reformer core. An outlet flow channel transports the resulting reformate stream containing reformed and thermally cracked hydrocarbons and substantial amounts of hydrogen out of the reformer core for later combination with the main combustor feed. Because the catalytic partial oxidation reaction in the reformer is highly exothermic, the additional heat is transferred (and thermally integrated) using one or more heat exchange units for a first and/or second auxiliary gas turbine fuel stream that undergo thermal cracking and vaporization before combining with the reformate. The combined, hydrogen-enriched feed significantly improves combustor performance. | 07-26-2012 |
20120291352 | Fluid Cooled Reformer and Method for Cooling a Reformer - The present subject matter discloses a fluid cooled reformer for gas turbine systems and a method for cooling both a fuel reformer and a heated reformate stream produced by such fuel reformer. The fluid cooled reformer may include a pressure vessel and a reactor assembly disposed within the pressure vessel, The reactor assembly may include a reactor and may be configured to receive and reform an oxygen/fuel mixture to produce a heated reformate stream. Additionally, the fluid cooled reformer may include an inlet configured to direct a fluid stream into the pressure vessel. At least a portion of the fluid stream may be used to cool the reactor assembly. A reformate cooling section may be disposed downstream of the reactor of the reactor assembly and may be configured to cool the heated reformate stream. | 11-22-2012 |
20120297784 | SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE - A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an airflow guide vane disposed in the air passage. The airflow guide vane includes an upstream vane portion and a downstream vane portion. The upstream vane portion is oriented at an angle from an axial axis of the gas turbine combustor. The downstream vane portion is aligned with the axial axis. The airflow guide vane is configured to remove a circumferential swirl of an airflow upstream of the airflow guide vane to straighten the airflow downstream of the airflow guide vane along the axial axis. | 11-29-2012 |
20120297785 | SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE - A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The structure obstructs an airflow through the air passage. The gas turbine combustor also includes a wake reducer disposed adjacent the structure. The wake reducer directs a flow into a wake region downstream of the structure. | 11-29-2012 |
20120297786 | SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE - A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, a fuel injector disposed downstream of the combustion liner and the flow sleeve, a liner mount extending between the combustion liner and the flow sleeve, and a crossfire tube extending between the combustion liner and the flow sleeve. The fuel injector, the liner mount, and the crossfire tube are aligned with one another in a flow enhancing arrangement along a common axis in an axial direction relative to an axis of the gas turbine combustor. The flow enhancing arrangement reduces an air flow disturbance caused by the fuel injector, the liner mount, and the crossfire tube. | 11-29-2012 |
20130036743 | TURBOMACHINE COMBUSTOR ASSEMBLY - A combustor assembly includes a combustor body having a combustion chamber, and a nozzle support mounted to the combustor body. The nozzle support includes a central opening, and a plurality of openings extending about the central opening. A central flame tolerant nozzle assembly is positioned within the central opening, and a plurality of micro-mixer nozzle assemblies are mounted in respective ones of the plurality of openings about the central flame tolerant nozzle assembly. Each of the central flame tolerant nozzle assembly and the plurality of micro-mixer nozzle assemblies are configured and disposed to deliver an air-fuel mixture into the combustion chamber. | 02-14-2013 |
20130074471 | TURBINE COMBUSTOR AND METHOD FOR TEMPERATURE CONTROL AND DAMPING A PORTION OF A COMBUSTOR - According to one aspect of the invention, a turbine combustor includes an outer member coupled to a wall of the combustor, wherein there is at least one damping hole formed in outer member. The turbine combustor further includes at least one temperature control hole formed in the wall wherein the at least one temperature control hole is formed at an angle with respect to a line perpendicular to a hot gas path in the combustor. | 03-28-2013 |
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 |
20130098053 | SYSTEMS AND METHODS FOR USE IN OPERATING TURBINE ENGINES - A control system for use with a turbine engine that is configured to operate at a rated power output is provided. The control system includes a computing device that includes a processor that is programmed to calculate an amount of fluid to be supplied for combustion in the turbine engine. The processor is also programmed to designate at least one nozzle of a plurality of nozzles to receive the fluid. Moreover, the control system includes at least one control valve coupled to the computing device. The control valve is configured to receive at least one control parameter from the computing device for use in modulating the amount of the fluid to be channeled to the nozzle such that the rated power output is generated while emission levels are maintained below a predefined emissions threshold level. | 04-25-2013 |
20130111909 | Combustion System Having A Venturi For Reducing Wakes In An Airflow - A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow. | 05-09-2013 |
20130115566 | COMBUSTOR HAVING WAKE AIR INJECTION - A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane. | 05-09-2013 |
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 |
20130125553 | Swirler Assembly with Compressor Discharge Injection to Vane Surface - A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes. | 05-23-2013 |
20130205799 | Outer Fuel Nozzle Inlet Flow Conditioner Interface to End Cap - An interface between an inlet flow conditioner and a compressor discharge air passage in a gas turbine includes a cap back plate including a curved exterior surface, and an inlet flow conditioner (IFC) cooperable with the cap back plate. An end of the IFC includes a curved exterior surface that is continued from the curved exterior surface of the cap back plate. The interface provides for more uniform and higher pressure air as well as more air supply, resulting in more uniform combustion. | 08-15-2013 |
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 |
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 |
20140130477 | TURBOMACHINE AND STAGED COMBUSTION SYSTEM OF A TURBOMACHINE - A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes. | 05-15-2014 |
20140325989 | Combustor with Fuel Staggering for Flame Holding Mitigation - The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit. | 11-06-2014 |