Patent application number | Description | Published |
20080276622 | FUEL NOZZLE AND METHOD OF FABRICATING THE SAME - A fuel nozzle includes a swirler assembly including a radially inner surface and a radially outer surface, a plurality of vanes coupled to the swirler assembly radially outer surface. Each vane includes a first sidewall and a second sidewall, the first and second sidewalls are joined at a leading edge and at an axially-spaced trailing edge, and a plurality of openings are formed through each respective vane. Each opening extends from the leading edge to the passage to define a flow passage that extends from the passage to the leading edge. A method for fabricating a fuel nozzle assembly is also described. | 11-13-2008 |
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 |
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 |
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 |
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 |
20110016866 | APPARATUS FOR FUEL INJECTION IN A TURBINE ENGINE - In one embodiment, a system includes a fuel injector including a liquid fuel passage extending to a first port in a tip portion. The fuel injector also includes a selectable flow passage extending to a second port in the tip portion. The selectable flow passage surrounds the liquid fuel passage to the tip portion, the selectable flow passage is configured to selectively receive a gas fuel flow and an air flow, and the selectable flow passage has a flow temperature configured to cool a liquid fuel flowing through the liquid fuel passage to reduce coking. | 01-27-2011 |
20110113783 | PREMIXING APPARATUS FOR FUEL INJECTION IN A TURBINE ENGINE - In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air. | 05-19-2011 |
20110262334 | SYSTEM AND METHOD FOR CONTROLLING AND REDUCING NOx EMISSIONS - Methods and systems are provided for reducing NOx emissions from a gas stream produced by a production source. The method may comprise oxidizing a substantial portion of NO gas present in the gas stream by contacting the gas stream with an oxidation catalyst to yield higher order N | 10-27-2011 |
20110265482 | POCKETED AIR AND FUEL MIXING TUBE - An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define a ring-like, annular path for the flow of fuel between the two hollow cylinders in each mixing tube, a plurality of air injection slots formed in the concentric hollow cylinders defining corresponding air flow paths from the outside into the interior of each mixing tube, and one or more fuel injection ports formed in selected ones of the plurality of air injection slots that allow for the flow of fuel from the annular path formed by the hollow cylinders into the air flow path, resulting in significantly better mixing and improved thermodynamic behavior of the fuel and air mixture downstream of the nozzle and upstream of the combustor. | 11-03-2011 |
20120073302 | FUEL NOZZLE ASSEMBLY FOR GAS TURBINE SYSTEM - A fuel nozzle assembly is disclosed. The fuel nozzle assembly comprises an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween. The fuel nozzle assembly further comprises a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus. The fuel nozzle assembly further comprises an air injection feature configured to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube. | 03-29-2012 |
20120291447 | COMBUSTOR NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor nozzle includes a first and second liquid fuel passages that terminate at first and second fuel ports. A first diluent passage terminates at a first diluent outlet radially surrounding the second fuel ports. A second diluent passage terminates at a second diluent outlet between the first diluent outlet and the second fuel ports. A third diluent passage surrounds at least a portion of the first and second diluent passages. A method for supplying fuel to a combustor includes flowing a liquid fuel through a first fuel passage and flowing an emulsified liquid fuel through a second fuel passage. The method further includes flowing a first diluent through a shroud surrounding the second fuel passage to a first diluent passage surrounding at least a portion of the second fuel passage and flowing a second diluent through a second diluent passage radially disposed between the first diluent passage and the second fuel passage. | 11-22-2012 |
20120305086 | SYSTEM AND METHOD FOR SUPPLYING FUEL - A system for supplying fuel includes a fuel manifold, a water manifold, and a fluid junction between the fuel manifold and the water manifold. A turbulator downstream from the fluid junction receives a fluid flow from the fluid junction. A method for supplying fuel includes flowing fuel through a fuel manifold, flowing water through a water manifold, and combining a portion of the water from the water manifold with the fuel from the fuel manifold to create emulsion fuel. The method further includes flowing the emulsion fuel through a turbulator. | 12-06-2012 |
20130047619 | INJECTION NOZZLE ASSEMBLY FOR A GAS TURBOMACHINE - An injection nozzle assembly includes a nozzle body having an outer surface and an inner surface that defines a flow passage, and a center body arranged within the nozzle body and extending along the flow passage. The center body includes a first end that extends to a tip portion through an intermediate portion that defines a fluid passage. The intermediate portion includes a first outer dimension and the tip portion includes a second outer dimension that is distinct from the first outer dimension. The center body includes a plurality of grooves that extend axially along the tip portion. | 02-28-2013 |
20130084534 | COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes. | 04-04-2013 |
20130098040 | SYSTEM FOR TURBINE COMBUSTOR FUEL ASSEMBLY - A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel. | 04-25-2013 |
20130167954 | FUEL DISTRIBUTION MANIFOLD - A fuel distribution manifold comprises an outer shell having an inner surface. The outer shell defines an inlet for receiving fuel from a parent supply line, a base opposite the inlet, a central manifold axis that intersects the inlet, and a plurality of outlets for delivering fuel to offspring fuel lines, each outlet defining a respective outlet axis. In one exemplary embodiment, a fuel distribution manifold also comprises a center-body having an outer surface and being positioned within the outer shell wherein the outer surface of the center-body and the inner surface of the outer shell define a flow-path through which fluid flows from the inlet to the plurality of outlets. In another exemplary embodiment, at least one of the outlets is positioned adjacent to the base and oriented so that its respective outlet axis is rotated relatively to a radial direction that intersects the central manifold axis. | 07-04-2013 |
20130174563 | COMBUSTOR FUEL NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor fuel nozzle includes a center body and an inner shroud that circumferentially surrounds at least a portion of the center body. The inner shroud has a downstream surface. The fuel nozzle includes an inner passage between the center body and the inner shroud, an outer passage that circumferentially surrounds at least a portion of the inner shroud and a first plurality of fuel ports extending substantially radially outward through the center body. The first plurality of fuel ports is upstream from the downstream surface of the inner shroud. A method for supplying fuel to a combustor fuel nozzle includes flowing a working fluid through an inner passage between a center body and an inner shroud, injecting a fuel from the center body against the inner shroud, and flowing a portion of the working fluid through an outer passage that surrounds at least a portion of the inner shroud. | 07-11-2013 |
20130177858 | COMBUSTOR AND METHOD FOR DISTRIBUTING FUEL IN THE COMBUSTOR - A combustor includes a plurality of tubes arranged in a tube bundle and supported by at least one plate that extends radially within the combustor, wherein each tube includes an upstream end axially separated from a downstream end and provides fluid communication through the tube bundle. A flow conditioner extends upstream from the upstream end of one or more of the plurality of tubes, and a radial passage extends through the flow conditioner. A method for distributing fuel in a combustor including flowing a working fluid through a flow conditioner that extends from a tube that is configured in a tube bundle comprising a plurality of tubes and that is supported by at least one plate. The flow conditioner includes at least one radial passage to impart radial swirl to the working fluid. Flowing a fuel through an annular insert that is at least partially surrounded by the flow conditioner. | 07-11-2013 |
20130186094 | Axial Flow Fuel Nozzle with a Stepped Center Body - An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings. | 07-25-2013 |
20130192236 | Method For Transferring Fuel - A method for transferring fuel includes flowing water to at least one nozzle of a main fuel circuit. Also included is flowing oil to the at least one nozzle of the main fuel circuit. Further included is flowing liquid fuel to the at least one nozzle of the main fuel circuit, wherein flowing water to the at least one nozzle of the main fuel circuit occurs prior to flowing oil to the at least one nozzle of the main fuel circuit and flowing liquid fuel to the at least one nozzle of the main fuel circuit. | 08-01-2013 |
20130219899 | ANNULAR PREMIXED PILOT IN FUEL NOZZLE - A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits. | 08-29-2013 |
20130283801 | SYSTEM FOR SUPPLYING FUEL TO A COMBUSTOR - A system for supplying fuel to a combustor includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber. A plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber. A liquid fuel plenum provides fluid communication to the plurality of passages. A baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum. | 10-31-2013 |
20130312422 | Liquid Cartridge with Passively Fueled Premixed Air Blast Circuit for Gas Operation - A gas/liquid fuel nozzle assembly includes a premixing tube bundle having an array of mixing tubes, a fuel plenum delivering fuel to the mixing tubes, a cartridge tube disposed within the fuel plenum, and a liquid fuel cartridge disposed in the cartridge tube. The liquid fuel cartridge is spaced from the cartridge tube to define an annulus. The cartridge tube and the fuel plenum are constructed in fluid communication such that gas fuel in the plenum is injected into the annulus. | 11-28-2013 |
20130318992 | Combustor with a Brief Severe Quench Zone - The present application provides a combustor for combusting a number of flows of air and a number of flows of fuel. The combustor may include a central swirler for producing a high swirl quench air flow, a number of trapped vortex cavities surrounding the central swirler for producing a flow of combustion gases, a brief severe quench zone downstream of the trapped vortex cavities to quench the flow of combustion gases between an outer quench air flow and the high swirl quench air flow, and an expansion zone downstream of the brief severe quench zone. | 12-05-2013 |
20140060063 | Systems and Methods For Suppressing Combustion Driven Pressure Fluctuations With a Premix Combustor Having Multiple Premix Times - A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles. | 03-06-2014 |
20140097276 | FUEL NOZZLE AND METHOD OF ASSEMBLING THE SAME - A fuel nozzle is provided. The fuel nozzle includes a nozzle body, a plurality of swirler vanes, and at least one outlet. The nozzle body includes a back plate, a front plate, and a mixing zone defined therebetween. The back plate includes at least one inlet defined therein and the front plate includes at least one discharge defined therein. The plurality of swirler vanes are positioned between the back plate and the front plate and spaced circumferentially about the mixing zone. Each of the plurality of swirler vanes direct air obliquely into the mixing zone. The at least one outlet is defined within at least one of the nozzle body and the plurality of swirler vanes, the at least one outlet configured to inject fuel into said mixing zone. | 04-10-2014 |
20140116054 | RADIAL FLOW FUEL NOZZLE FOR A COMBUSTOR OF A GAS TURBINE - A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold. | 05-01-2014 |
20140123653 | ENHANCEMENT FOR FUEL INJECTOR - A fuel injector is provided and includes a surface disposed proximate to a flow of a first fluid and a delta wing feature. The surface has upstream and downstream portions defined relative to the flow and defines an injector hole in the downstream portion by which a jet of a second fluid is injectable into the flow. The delta wing feature is disposed on the surface at the upstream portion and is configured to lift an oncoming portion of the flow off the surface and to cause the oncoming portion of the flow to form a pair of counter-rotating vortices that respectively co-rotate with the jet in a cross-flow direction. | 05-08-2014 |
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 |
20140144150 | 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 a fuel injector configured to discharge a flow of fuel therefrom and a premixer tube coupled in flow communication with the fuel injector. The premixer tube is configured to receive the fuel flow and a flow of air at an upstream end of the premixer tube, wherein the fuel and air are progressively mixed as the fuel and air are channeled through the length of the premixer tube. | 05-29-2014 |
20140190170 | FUEL INJECTOR FOR SUPPLYING FUEL TO A COMBUSTOR - A fuel injector for a combustor generally includes an annular outer body having an inlet and an outlet. The outer body at least partially defines an outer flow passage. An inner flow passage extends at least partially through the outer flow passage and a radial swirler is disposed at the inlet of the outer body. The radial swirler includes a first radial passage separated from a second radial passage. The first radial passage has a first plurality of swirler vanes and the second radial passage has a second plurality of swirler vanes. The first radial passage is in fluid communication with the outer flow passage and the second radial passage is in fluid communication with the inner flow passage. | 07-10-2014 |
20140190174 | MICROMIXER ASSEMBLY FOR A TURBINE SYSTEM AND METHOD OF DISTRIBUTING AN AIR-FUEL MIXTURE TO A COMBUSTOR CHAMBER - A micromixer assembly for a turbine system includes a plurality of pipes each having an inlet for receiving an airflow from an annulus defined by an inwardly disposed liner and an outwardly disposed sleeve, each of the plurality of pipes also including an outlet for dispersing an air-fuel mixture into a combustor chamber. Also included is a first portion of each of the plurality of pipes. Further included is a second portion of each of the plurality of pipes, the second portion comprising the inlet for receiving the airflow. Yet further included is at least one fuel receiving path in communication with at least one of the first portion and the second portion. | 07-10-2014 |
20140238026 | FUEL NOZZLE FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS - A fuel nozzle includes a center body that extends axially along an axial centerline for a length. A shroud circumferentially surrounds the center body for at least a portion of the length of the center body. A plurality of helical passages circumferentially surround the center body along at least a portion of the length of the center body, and a fuel port in each helical passage has a different convective time. | 08-28-2014 |
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 |
20140260299 | FUEL-AIR MIXING SYSTEM FOR GAS TURBINE SYSTEM - Embodiments of the present disclosure are directed to systems and methods for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of fuel injectors and a plurality of mixing tubes, wherein each mixing tube has a first portion for receiving one of the plurality of fuel injectors and a second portion having a mixing chamber that is configured to mix fuel and air. The length of the mixing chamber varies among the plurality of mixing tubes to allow for different mixing times. | 09-18-2014 |
20140260300 | AIR DIFFUSER FOR COMBUSTOR - A system includes a multi-tube fuel nozzle of a turbine combustor. The multi-tube fuel nozzle 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 an outer annular wall configured to direct an air flow from an annulus between a liner and a flow sleeve of the turbine combustor at least partially radially inward into the interior volume through an air inlet and toward the plurality of mixing tubes, wherein the outer annular wall at least partially defines an air flow passage extending from the annulus to the interior volume. | 09-18-2014 |
20140260315 | SYSTEM HAVING MULTI-TUBE FUEL NOZZLE WITH FLOATING ARRANGEMENT OF MIXING TUBES - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes an end cover, a first plate, and multiple tubes. The multiple tubes are disposed and supported in a floating arrangement between the end cover and the first plate. Each tube includes a forward end adjacent the end cover and an aft end adjacent the first plate. | 09-18-2014 |
20140283522 | MULTI-INJECTOR MICROMIXING SYSTEM - Embodiments of the present disclosure are directed to a system having components for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of mixing tubes configured to receive and to mix fuel and air. Each mixing tube is paired with a fuel injector, and the fuel injector is positioned axially within a portion of the mixing tube. Fuel is injected from the fuel injector into the respective mixing tube, and air flows radially into each mixing tube through one or more apertures formed on the mixing tube. The fuel and air are mixed within the mixing tube and are deposited into a combustion chamber for combustion. | 09-25-2014 |
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 |
20140338340 | SYSTEM AND METHOD FOR TUBE LEVEL AIR FLOW CONDITIONING - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple tubes. Each tube includes a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be disposed about a fuel injector. Each tube also includes an air flow conditioner having multiple air ports disposed adjacent the first end. The multiple air ports extend through the wall into the central passage. | 11-20-2014 |