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 |
20090120093 | Turbulated aft-end liner assembly and cooling method - In a combustor for a turbine a cover sleeve is disposed between the aft end portion of the combustor liner and a resilient seal structure to define an air flow passage therebetween. The cover sleeve has at a forward end thereof a plurality of air inlet feed holes for directing cooling air into the air flow passage. A radially outer surface of the combustor liner aft end portion defining the air flow passage includes a plurality of turbulators projecting towards but spaced from the cover sleeve and a plurality of supports extending to and engaging the cover sleeve to space the cover sleeve from the turbulators to define the air flow passage. | 05-14-2009 |
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 |
20090235668 | Insulator bushing for combustion liner - A combustor for a turbine including: a combustor liner, a first flow sleeve surrounding the combustor liner to define a first flow annulus, the first flow sleeve having cooling holes for directing compressor discharge air as cooling air into the first flow annulus, a transition piece body connected to the combustor liner to carry hot combustion gases to the turbine; a second flow sleeve surrounding the transition piece body, the second flow sleeve having cooling holes for directing compressor discharge air as cooling air into a second flow annulus between the second flow sleeve and the transition piece body; at least one dilution hole in the combustor liner for flowing compressor air into a combustion chamber defined by the combustor liner; and a bushing seated in at least one of the cooling or dilution holes and secured with respect thereto for defining a flow passage for compressor discharge air through the hole. | 09-24-2009 |
20090320483 | Variable Orifice Plug for Turbine Fuel Nozzle - A fuel nozzle for use about an end cap of a combustor. The fuel nozzle may include a flange attached to the end cap, an aperture extending through the flange, a plug positioned in the aperture, and an orifice positioned within the plug. | 12-31-2009 |
20100077761 | IMPINGEMENT COOLED COMBUSTOR SEAL - Disclosed is a combustor seal including a seal support locatable at a first combustor component and having a plurality of through impingement holes. A wave-shaped seal located at the seal support and defining at least one seal cavity between the wave-shaped seal and the seal support. A peak of the wave-shaped seal is locatable at a second combustor component. The wave-shaped seal includes at least one through passageway located upstream of the peak capable of flowing cooling fluid therethrough into the at least one seal cavity and through the plurality of impingement holes thereby cooling the first combustor component. Further disclosed is a combustor including a combustor seal and a method for cooling a first combustor component. | 04-01-2010 |
20100084490 | Premixed Direct Injection Nozzle - An injection nozzle having a main body portion with an outer peripheral wall is disclosed. The nozzle includes a plurality of fuel/air mixing tubes disposed within the main body portion and a fuel flow passage fluidly connected to the plurality of fuel/air mixing tubes. Fuel and air are partially premixed inside the plurality of the tubes. A second body portion, having an outer peripheral wall extending between a first end and an opposite second end, is connected to the main body portion. The partially premixed fuel and air mixture from the first body portion gets further mixed inside the second body portion. The second body portion converges from the first end toward said second end. The second body portion also includes cooling passages that extend along all the walls around the second body to provide thermal damage resistance for occasional flame flash back into the second body. | 04-08-2010 |
20100089367 | FUEL NOZZLE ASSEMBLY - A fuel nozzle assembly is provided. The assembly includes an outer nozzle body having a first end and a second end and at least one inner nozzle tube having a first end and a second end. One of the nozzle body or nozzle tube includes a fuel plenum and a fuel passage extending therefrom, while the other of the nozzle body or nozzle tube includes a fuel injection hole slidably aligned with the fuel passage to form a fuel flow path therebetween at an interface between the body and the tube. The nozzle body and the nozzle tube are fixed against relative movement at the first ends of the nozzle body and nozzle tube, enabling the fuel flow path to close at the interface due to thermal growth after a flame enters the nozzle tube. | 04-15-2010 |
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 |
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 |
20100154436 | Forward sleeve retainer plate and method - In a combustor section, wherein a forward sleeve is disposed to encircle a leading end of an impingement sleeve comprised of first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal junction. The retainer member is welded to at least one of said forward sleeve and the impingement sleeve. The retainer member has first and second axial end edges disposed transverse to the longitudinal junction, and at least one of the axial end edges has a cutout defined therein and disposed to overlie the longitudinal junction. | 06-24-2010 |
20100175380 | TRAVERSING FUEL NOZZLES IN CAP-LESS COMBUSTOR ASSEMBLY - A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention. | 07-15-2010 |
20100180602 | COMBUSTOR ASSEMBLY AND CAP FOR A TURBINE ENGINE - A combustor assembly for a turbine engine includes a cap assembly which gradually increases the volume of compressed air provided to the combustor assembly, and which slows the compressed air in a controlled manner before delivering the compressed air into a combustor area. The cap assembly includes inner and outer sleeves which are mounted in a concentric fashion. The annular space formed between the inner and outer sleeves gradually increases from an aft end to a forward end. A stepped portion is formed on the inner sleeve of the cap assembly, and this stepped portion is joined to a corresponding combustor liner. | 07-22-2010 |
20100186413 | BUNDLED MULTI-TUBE 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 cap member having a first surface that extends to a second surface. The cap member further includes a plurality of openings. A plurality of bundled mini-tube assemblies are detachably mounted in the plurality of openings in the cap member. Each of the plurality of bundled mini-tube assemblies includes a main body section having a first end section and a second end section. A fluid plenum is arranged within the main body section. A plurality of tubes extend between the first and second end sections. Each of the plurality of tubes is fluidly connected to the fluid plenum. | 07-29-2010 |
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 |
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 |
20100236247 | METHOD AND APPARATUS FOR DELIVERY OF A FUEL AND COMBUSTION AIR MIXTURE TO A GAS TURBINE ENGINE - A nozzle has combustion air passages extending from a first, upstream end to a second, downstream end. A fuel distribution manifold is associated with the first, upstream end of the nozzle. Combustion air passages correspond to, and align with the air passages in the nozzle. Fuel distribution grooves are formed in one end of the fuel distribution manifold disk and extend from a central opening to the air passages. A fuel circuit cover closes the fuel distribution grooves to define fuel passages that extend from the central opening to the combustion air passages. A fuel supply conduit communicates with the central opening and the fuel passages for delivery of fuel to the combustion air in the air passages. | 09-23-2010 |
20100236249 | Systems and Methods for Reintroducing Gas Turbine Combustion Bypass Flow - A system and method for reintroducing gas turbine combustion bypass flow. The system may include a combustor body, wherein the combustor body includes a reaction zone for primary combustion of fuel and air, and a casing enclosing the combustor body and defining an annular passageway for carrying compressor discharge air into the combustor body at one end. The system further may include a reintroduction manifold for receiving combustor bypass air extracted from the compressor discharge air in the annular passageway, and one or more reintroduction slots in communication with the reintroduction manifold for injecting the combustor bypass air into the combustor body downstream of the reaction zone. The method may include extracting combustor bypass air from the annular passageway, transporting the combustor bypass air to a reintroduction manifold, and reintroducing the combustor bypass air into the combustor body through one or more reintroduction slots in communication with the reintroduction manifold. | 09-23-2010 |
20100252652 | PREMIXING DIRECT INJECTOR - A fuel injection nozzle comprises a body member having an upstream wall opposing a downstream wall, a baffle member having an upstream surface and a downstream surface, a first chamber, a second chamber, a fuel inlet communicative with the first chamber operative to emit a first gas into the first 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 second gas, a second inlet communicative with the tube outer surface and the tube inner surface operative to translate the first gas into the mixing tube, a mixing portion operative to mix the first gas and the second gas, and an outlet communicative with an aperture in the downstream wall operative to emit the mixed first and second gasses. | 10-07-2010 |
20100263383 | GAS TURBINE PREMIXER WITH INTERNAL COOLING - A system that includes a turbine fuel nozzle comprising an air-fuel premixer. The air-fuel premixed includes a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises an internal coolant path from a downstream end portion in an upstream direction through a substantial length of the swirl vane. | 10-21-2010 |
20100263386 | TURBINE ENGINE HAVING A LINER - In one embodiment, a combustor of a turbine system may include a liner disposed inside the combustor. The lining element may include a heat shield having a mounting stud extending along an axis and a shell having an inner surface oriented towards the heat shield. The shell may include a passage configured to receive the mounting stud, and the mounting stud may include a structure configured to hold the heat shield apart from the inner surface of the shell along the axis of the mounting stud. | 10-21-2010 |
20100300106 | SYSTEM AND METHOD FOR THERMAL CONTROL IN A CAP OF A GAS TURBINE COMBUSTOR - A system comprises a turbine combustor cap. The turbine combustor cap includes a plurality of segments. Each segment of the plurality of segments has edges abutting at least two fuel nozzle receptacles. Moreover, each segment of the plurality of segments does not completely surrounding any one fuel nozzle receptacle. | 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 |
20110000214 | METHODS AND SYSTEMS TO THERMALLY PROTECT FUEL NOZZLES IN COMBUSTION SYSTEMS - A method of assembling a gas turbine engine is provided. The method includes coupling a combustor in flow communication with a compressor such that the combustor receives at least some of the air discharged by the compressor. A fuel nozzle assembly is coupled to the combustor and includes at least one fuel nozzle that includes a plurality of interior surfaces, wherein a thermal barrier coating is applied across at least one of the plurality of interior surfaces to facilitate shielding the interior surfaces from combustion gases. | 01-06-2011 |
20110067404 | Universal Multi-Nozzle Combustion System and Method - A gas turbine combustion system includes a supporting fuel manifold including a plurality of fuel nozzle support openings and a plurality of fuel line passages, and an aft case defining at least part of a combustion zone. The supporting fuel manifold is connected to the aft case. A plurality of fuel nozzles are supported one each in the plurality of fuel nozzle support openings, and a plurality of fuel lines communicate with the plurality of fuel line passages. The plurality of fuel lines deliver fuel to the plurality of fuel nozzles via the plurality of fuel line passages. | 03-24-2011 |
20110072824 | APPARTUS AND METHOD FOR A GAS TURBINE NOZZLE - A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downstream of the inlet, and the circumference at the first point downstream of the inlet is less than the circumference at a second point downstream of the first point. A method for supplying a fuel through a nozzle directs a first airflow along a first path and a second airflow along a second path separate from the first path. The method further includes injecting the fuel into at least one of the first path or the second path and accelerating at least one of the first airflow or the second airflow. | 03-31-2011 |
20110073684 | INTERNAL BAFFLING FOR FUEL INJECTOR - A fuel injector includes a fuel delivery tube; a plurality of pre-mixing tubes, each pre-mixing tube comprising at least one fuel injection hole; an upstream tube support plate that supports upstream ends of the plurality of pre-mixing tubes; a downstream tube support plate that supports downstream ends of the plurality of pre-mixing tubes; an outer wall connecting the upstream tube support plate and the downstream tube support plate and defining a plenum therewith; and a baffle provided in the plenum. The baffle includes a radial portion. A fuel delivered in the upstream direction by the fuel delivery tube is directed radially outwardly in the plenum between the radial portion of the baffle and the downstream tube support plate, then in the downstream direction around an outer edge portion of the radial portion, and then radially inwardly between the radial portion and the upstream tube support plate. | 03-31-2011 |
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 |
20110107769 | IMPINGEMENT INSERT FOR A TURBOMACHINE INJECTOR - A turbomachine includes a compressor, a turbine operatively coupled to the compressor, and a combustion assembly fluidly linking the compressor and the turbine. The combustion assembly includes at least one injector having a burner tube including an outer wall portion and an inner wall portion that define a mixing zone. A swirler arranged within the mixing zone. The swirler includes a plurality of vanes, with at least one of the plurality of vanes having a wall section including an outer surface and an inner surface that define a hollow interior portion. An insert member is arranged within the hollow interior portion. The insert member includes at least one guide element that is disposed and configured to deliver a fluid flow to the hollow interior portion to flow over the wall section of the at least one of the plurality of vanes. | 05-12-2011 |
20110120135 | TURBULATED AFT-END LINER ASSEMBLY AND COOLING METHOD - A turbine includes a transition portion where a combustor section joins a transition piece. The combustor section includes a combustor liner having an aft end that joins a transition piece body of the transition piece. A reduced thickness portion at the aft end of the combustor liner is covered by a cover sleeve to form an air flow passage on the aft end of the combustor liner. Apertures in the forward portion of the cover sleeve allow cooling air to flow into air flow passage. A plurality of turbulators project radially outward from the reduced thickness portion of the combustor sleeve towards said cover sleeve. An arch shaped resilient seal structure is positioned between the cover sleeve and the transition piece body. Supports formed on the reduced thickness portion of the combustor liner bear against the inside of the cover sleeve to prevent the cover sleeve from deforming inward due to a force applied by the seal, thereby ensuring that the air flow passage remains open. | 05-26-2011 |
20110179795 | INJECTOR WITH INTEGRATED RESONATOR - The system may include a turbine engine. The turbine engine may include a fuel nozzle. The fuel nozzle may include an air path. The fuel nozzle may also include a fuel path such that the fuel nozzle is in communication with a combustion zone of the turbine engine. Furthermore, the fuel nozzle may include a resonator. The resonator may be disposed in the fuel nozzle directly adjacent to the combustion zone. | 07-28-2011 |
20110197587 | MULTI-TUBE PREMIXING INJECTOR - A fuel injection nozzle includes at least one tube disposed in the nozzle having a venturi shaped profile defining a gas flow path including an inlet operative to receive a first gas, at least one port operative to emit a second gas into the gas flow path, and an outlet operative to emit a mixture of the first gas and the second gas into a combustor. | 08-18-2011 |
20110225947 | SYSTEM AND METHODS FOR ALTERING AIR FLOW IN A COMBUSTOR - A combustor assembly of a turbine engine is provided with a mechanical air regulation unit which selectively varies the amount of air being delivered into a combustion zone of the combustor based upon a pressure of a fuel being supplied to the combustor. A first type of air regulation unit would act to increase the amount of air entering the combustion zone when greater amounts of a high heat value fuel are being delivered to the fuel nozzles of the combustor. A second type of air regulation unit could act to decrease the amount of air entering the combustion zone when greater amounts of a low heat value fuel are being delivered into the combustor through fuel nozzles. | 09-22-2011 |
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 |
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 |
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 |
20120023895 | APPARATUS AND FILTERING SYSTEMS RELATING TO COMBUSTORS IN COMBUSTION TURBINE ENGINES - A combustor for a combustion turbine engine, the combustor that includes: a chamber defined by an outer wall and forming a channel between windows defined through the outer wall toward a forward end of the chamber and at least one fuel injector positioned toward an aft end of the chamber; a screen; and a standoff comprising a raised area on an outer surface of the outer wall near the periphery of the windows; wherein the screen extends over the windows and is supported by the standoff in a raised position in relation to the outer surface of the outer wall and the windows. | 02-02-2012 |
20120023949 | APPARATUS AND FILTERING SYSTEMS RELATING TO COMBUSTORS IN COMBUSTION TURBINE ENGINES - A combustor for a combustion turbine engine that includes: a chamber defined by an outer wall and forming a channel between windows defined through the outer wall toward a forward end of the chamber and at least one fuel injector positioned toward an aft end of the chamber; and a multilayer screen filter comprising at least two layers of screen over at least a portion of the windows and at least one layer of screen over the remaining portion of the windows. The windows include a forward end and a forward portion, and an aft end and an aft portion. The multilayer screen filter is positioned over the windows such that, in operation, a supply of compressed air entering the chamber through the windows passes through at least one layer of screen. The multilayer screen filter is configured such that the aft portion of the windows include at least two layers of screen, and the forward portion of the windows includes one less layer of screen than the aft portion of the windows. | 02-02-2012 |
20120024985 | INTEGRATED FUEL NOZZLE AND INLET FLOW CONDITIONER AND RELATED METHOD - A nozzle center body includes a unitary, one-piece, elongated tubular member having a forward end formed with a radially outwardly extending mounting flange; an aft end formed with a plurality of radially outwardly extending swirler vanes; and, an intermediate region, located axially between the forward and aft ends, formed with an inlet flow conditioner including an annular plate provided with plural, circumferentially-spaced flow openings therein. A related method of forming the nozzle center body by casting is also disclosed. | 02-02-2012 |
20120031102 | TURBINE COMBUSTOR WITH FUEL NOZZLES HAVING INNER AND OUTER FUEL CIRCUITS - A combustor cap assembly for a turbine engine includes a combustor cap and a plurality of fuel nozzles mounted on the combustor cap. One or more of the fuel nozzles would include two separate fuel circuits which are individually controllable. The combustor cap assembly would be controlled so that individual fuel circuits of the fuel nozzles are operated or deliberately shut off to provide for physical separation between the flow of fuel delivered by adjacent fuel nozzles and/or so that adjacent fuel nozzles operate at different pressure differentials. Operating a combustor cap assembly in this fashion helps to reduce or eliminate the generation of undesirable and potentially harmful noise. | 02-09-2012 |
20120036856 | DIMPLED/GROOVED FACE ON A FUEL INJECTION NOZZLE BODY FOR FLAME STABILIZATION AND RELATED METHOD - A fuel injection head for a fuel nozzle used in a gas turbine combustor includes a substantially hollow body formed with an upstream end face, a downstream end face and a peripheral wall extending therebetween. A plurality of pre-mix tubes or passages extend axially through the hollow body with inlets at the upstream end face and outlets at the downstream end face. An exterior surface of the downstream end face is formed with three-dimensional surface features that increase a total surface area of the exterior surface as compared to a substantially flat, planar downstream end face. | 02-16-2012 |
20120055163 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A method for assembling a fuel injection assembly for use in a turbine engine is provided. The method includes providing at least one cap member that has at least one first opening extending at least partially through it and at least one second opening extending at least partially through it. The method includes coupling a plurality of tube assemblies within the turbine engine. Each tube assembly includes a plurality of tubes. Moreover, the method includes coupling an injection system to the cap member to enable a fluid from a fluid source to be discharged through the at least one second opening. This fluid provides a barrier between adjacent tube assemblies to facilitate reducing dynamic pressure oscillations within the fuel injection assembly during turbine engine operation. | 03-08-2012 |
20120055167 | APPARATUS AND METHOD FOR MIXING FUEL IN A GAS TURBINE NOZZLE - A nozzle includes a fuel plenum and an air plenum downstream of the fuel plenum. A primary fuel channel includes an inlet in fluid communication with the fuel plenum and a primary air port in fluid communication with the air plenum. Secondary fuel channels radially outward of the primary fuel channel include a secondary fuel port in fluid communication with the fuel plenum. A shroud circumferentially surrounds the secondary fuel channels. A method for mixing fuel and air in a nozzle prior to combustion includes flowing fuel to a fuel plenum and flowing air to an air plenum downstream of the fuel plenum. The method further includes injecting fuel from the fuel plenum through a primary fuel passage, injecting fuel from the fuel plenum through secondary fuel passages, and injecting air from the air plenum through the primary fuel passage. | 03-08-2012 |
20120058437 | APPARATUS AND METHOD FOR MIXING FUEL IN A GAS TURBINE NOZZLE - A nozzle includes a fuel plenum and an air plenum downstream of the fuel plenum. Fuel channels radially outward of an axial centerline of the nozzle include an inlet and an outlet downstream of the inlet. A fuel port in the fuel channels provides fluid communication between the fuel plenum and the fuel channels. An air port in the fuel channels downstream of the fuel port provides fluid communication between the air plenum and the fuel channels. A method for mixing fuel and air in a nozzle prior to combustion includes flowing fuel to a fuel plenum and flowing air to an air plenum downstream of the fuel plenum. The method further includes injecting fuel from the fuel plenum through fuel ports in fuel channels and injecting air from the air plenum through air ports in the fuel channels. | 03-08-2012 |
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 |
20120180495 | SYSTEM AND METHOD FOR INJECTING FUEL - According to various embodiments, a system includes a staggered multi-nozzle assembly. The staggered multi-nozzle assembly includes a first fuel nozzle having a first axis and a first flow path extending to a first downstream end portion, wherein the first fuel nozzle has a first non-circular perimeter at the first downstream end portion. The staggered multi-nozzle assembly also includes a second fuel nozzle having a second axis and a second flow path extending to a second downstream end portion, wherein the first and second downstream end portions are axially offset from one another relative to the first and second axes. The staggered multi-nozzle assembly further includes a cap member disposed circumferentially about at least the first and second fuel nozzles to assemble the staggered multi-nozzle assembly. | 07-19-2012 |
20120192566 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A method for assembling a fuel injection assembly for use in a turbine engine is provided. The method includes providing a cap assembly that has at least one first opening extending at least partially through it and a plurality of second openings extending at least partially through it. Moreover, a plurality of tube assemblies are coupled within the cap assembly. Each tube assembly includes a plurality of tubes. Further, at least one injection system is coupled to the cap assembly to enable a fluid from a fluid source to be discharged through at least one of the plurality of second openings. The fluid flows between at least two adjacent tube assemblies to facilitate at least one of reducing a temperature within the cap assembly and reducing dynamic pressure oscillations within a combustor during operation of the turbine engine. | 08-02-2012 |
20120198812 | APPARATUS FOR MIXING FUEL IN A GAS TURBINE - A combustor nozzle includes an inlet surface and an outlet surface downstream from the inlet surface, wherein the outlet surface has an indented central portion. A plurality of fuel channels are arranged radially outward of the indented central portion, wherein the plurality of fuel channels extend through the outlet surface. | 08-09-2012 |
20120198851 | TRAVERSING FUEL NOZZLES IN CAP-LESS COMBUSTOR ASSEMBLY - A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention. | 08-09-2012 |
20120255310 | COMBUSTOR NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define a passage between the center body and the shroud. A guide between the center body and the shroud can pivot with respect to the center body. A method for supplying fuel to a combustor includes flowing a working fluid through a nozzle at a mass flow rate and flowing a fuel through the nozzle. The method further includes sensing a flame holding event inside the nozzle and pivoting a guide inside the nozzle to increase the mass flow rate of the working fluid flowing through the nozzle. | 10-11-2012 |
20120279223 | Fuel Injector and Support Plate - An integrated plate is provided for use with a combustor including a casing, a fuel plenum extending circumferentially about the casing, and a fuel nozzle extending axially through the casing. The integrated plate includes a plurality of fuel injection pegs that extend radially between the fuel plenum and the fuel nozzle. | 11-08-2012 |
20130042625 | MICROMIXER HEAT SHIELD - A combustor includes a combustor wall defining a combustion zone and a fuel nozzle. The fuel nozzle includes a forward face, an aft face downstream from the forward face and adjacent to the combustion zone, a plurality of mixing tubes extending between the forward face and the aft face, an outer sleeve positioned radially outward of the plurality of mixing tubes, a heat shield positioned radially inward of the outer sleeve, and a baffle plate between the forward face and the aft face. At least one of the plurality of mixing tubes includes a sidewall that includes an injection opening defined therethrough. The baffle plate is oriented to channel fuel between the plurality of mixing tubes and between the baffle plate and the aft face prior to the fuel being channeled through the injection opening. | 02-21-2013 |
20130045450 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A COMBUSTOR - A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes. | 02-21-2013 |
20130061593 | SYSTEM AND METHOD FOR CONTROLLING A COMBUSTOR ASSEMBLY - A system and method for controlling a combustor assembly are disclosed. The system includes a combustor assembly. The combustor assembly includes a combustor and a fuel nozzle assembly. The combustor includes a casing. The fuel nozzle assembly is positioned at least partially within the casing and includes a fuel nozzle. The fuel nozzle assembly further defines a head end. The system further includes a viewing device configured for capturing an image of at least a portion of the head end, and a processor communicatively coupled to the viewing device, the processor configured to compare the image to a standard image for the head end. | 03-14-2013 |
20130104551 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME | 05-02-2013 |
20130104552 | FUEL NOZZLE ASSEMBLY FOR USE IN TURBINE ENGINES AND METHODS OF ASSEMBLING SAME | 05-02-2013 |
20130104556 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS AND NOX IN A COMBUSTOR | 05-02-2013 |
20130174568 | COMBUSTOR AND METHOD FOR DISTRIBUTING FUEL IN THE COMBUSTOR - A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface. A plurality of tubes extends from the upstream surface through the downstream surface, and each tube provides fluid communication through the tube bundle. A baffle extends axially inside the tube bundle between adjacent tubes. A method for distributing fuel in a combustor includes flowing a fuel into a fuel plenum defined at least in part by an upstream surface, a downstream surface, a shroud, and a plurality of tubes that extend from the upstream surface to the downstream surface. The method further includes impinging the fuel against a baffle that extends axially inside the fuel plenum between adjacent tubes. | 07-11-2013 |
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 |
20130199190 | 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 fuel delivery pipe and a fluid supply member coupled to the fuel delivery pipe, wherein the fluid supply member is positioned a predefined distance upstream from the tube assembly and includes at least one first portion having an annular end portion. The annular end portion includes at least one opening for delivering fluid toward the tube assembly for reducing dynamic pressure oscillations and/or reducing the temperature within a combustor during operation of the turbine engine. | 08-08-2013 |
20130227928 | FUEL NOZZLE ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel nozzle for use with a turbine engine is provided. The fuel nozzle includes a housing coupled to a combustor liner defining a combustion chamber. The housing is at least partially positioned within an air plenum and comprises an endwall that at least partially defines the air plenum. The fuel nozzle includes a plurality of mixing tubes extending through the housing for channeling a fuel to the combustion chamber, a cooling fluid plenum at least partially defined within the housing by the housing endwall, and a plurality of apertures defined within the housing endwall for channeling a cooling fluid from the cooling fluid plenum to the air plenum. | 09-05-2013 |
20130227953 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A COMBUSTOR - A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend from the upstream surface through the downstream surface. A divider inside a tube bundle defines a diluent passage that extends axially through the downstream surface, and a diluent supply in fluid communication with the divider provides diluent flow to the diluent passage. A method for reducing combustion dynamics in a combustor includes flowing a fuel through tube bundles, flowing a diluent through a diluent passage inside a tube bundle, wherein the diluent passage extends axially through at least a portion of the end cap into a combustion chamber, and forming a diluent barrier in the combustion chamber between the tube bundle and at least one other adjacent tube bundle. | 09-05-2013 |
20130227955 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A COMBUSTOR - A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend through the end cap. A diluent supply in fluid communication with the end cap provides diluent flow to the end cap. Diluent distributors circumferentially arranged inside at least one tube bundle extend downstream from the downstream surface and provide fluid communication for the diluent flow through the end cap. A method for reducing combustion dynamics in a combustor includes flowing fuel through tube bundles that extend axially through an end cap, flowing a diluent through diluent distributors into a combustion chamber, wherein the diluent distributors are circumferentially arranged inside at least one tube bundle and each diluent distributor extends downstream from the end cap, and forming a diluent barrier in the combustion chamber between at least one pair of adjacent tube bundles. | 09-05-2013 |
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 |
20130283806 | COMBUSTOR AND A METHOD FOR REPAIRING THE COMBUSTOR - A combustor generally includes a liner that at least partially defines a combustion chamber within the combustor. The liner may generally include a hole that extends through the liner and that at least partially defines a mating surface. An insert having an outer surface extends at least partially through the hole. A projection that at least partially defines a mating surface at least partially circumferentially surrounds the insert outer surface. A joint between the projection mating surface and the hole mating surface provides a connection point between the projection mating surface and the liner hole mating surface. | 10-31-2013 |
20130283807 | SYSTEM AND METHOD FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. Injectors circumferentially arranged around the flow sleeve provide fluid communication through the flow sleeve and into the combustion chamber. A valve upstream from the injectors has a first position that permits working fluid flow to the injectors and a second position that prevents working fluid flow to the injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through injectors circumferentially arranged around the combustion chamber, and operating a valve upstream from the injectors to control the working fluid flow through the injectors. | 10-31-2013 |
20130284825 | FUEL NOZZLE - A fuel nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. A plurality of vanes extend radially between the center body and the shroud in the annular passage. A first ceramic extension extends downstream from the shroud to define at least a portion of the annular passage downstream from the shroud. | 10-31-2013 |
20130298563 | Secondary Combustion System - The present application provides a secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine. The secondary combustion system may include a manifold ring and a number of injectors extending from the manifold ring. Each of the injectors may include a number of jets in communication with the manifold ring. One or more of the jets may include an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle. | 11-14-2013 |
20130299602 | SYSTEM AND METHOD HAVING MULTI-TUBE FUEL NOZZLE WITH DIFFERENTIAL FLOW - A system includes a multi-tube fuel nozzle with a fuel nozzle body and a plurality of tubes. The fuel nozzle body includes a nozzle wall surrounding a chamber. The plurality of tubes extend through the chamber, wherein each tube of the plurality of tubes includes an air intake portion, a fuel intake portion, and an air-fuel mixture outlet portion. The multi-tube fuel nozzle also includes a differential configuration of the air intake portions among the plurality of tubes. | 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 |
20130318977 | 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 an end cover, an endcap assembly, a fluid supply chamber, and a plurality of tube assemblies positioned at the endcap assembly. Each of the tube assemblies includes a housing having a fuel plenum and a cooling fluid plenum defined therein, the cooling fluid plenum downstream from the fuel plenum and separated therefrom by an intermediate wall, a plurality of tubes extending through the housing, each of the plurality of tubes in flow communication with the fluid supply chamber and a combustion chamber downstream from the tube assembly, and an aft plate at a downstream end of the cooling fluid plenum, the aft plate including at least one aperture defined therethrough. The fuel injection assembly further includes at least one fuel delivery pipe coupled to at least one of the plurality of tube assemblies. | 12-05-2013 |
20140013723 | SYSTEM AND METHOD OF SUPPLYING FUEL TO A GAS TURBINE - A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes. | 01-16-2014 |
20140020389 | COMBUSTOR CAP ASSEMBLY - One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion. | 01-23-2014 |
20140053571 | SEAL FOR A PERFORATED PLATE - A cooling circuit of a gas turbine passes an airflow through a combustor section that includes a plurality of mixing tubes for transporting a fuel/air mixture and a perforated plate including a plurality of impingement holes and a plurality of tube holes for accommodating the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the perforated plate and the mixing tubes. The impingement holes and the annulus areas are configured to pass the airflow through the perforated plate. A flow management device modifies an effective size of the annulus areas to control a distribution of the airflow through the impingement holes and the annulus areas of the perforated plate to enhance cooling efficiency. | 02-27-2014 |
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 |
20140144152 | Premixer With 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 |
20140157779 | SYSTEM FOR REDUCING COMBUSTION DYNAMICS AND NOx IN A COMBUSTOR - A combustor includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. 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. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion. | 06-12-2014 |
20140202163 | EFFUSION PLATE USING ADDITIVE MANUFACTURING METHODS - Additive manufacturing techniques may be utilized to construct effusion plates. Such additive manufacturing techniques may include defining a configuration for an effusion plate having one or more internal cooling channels. The manufacturing techniques may further include depositing a powder into a chamber, applying an energy source to the deposited powder, and consolidating the powder into a cross-sectional shape corresponding to the defined configuration. Such methods may be implemented to construct an effusion plate having one or more channels with a curved cross-sectional geometry. | 07-24-2014 |
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 |
20140216048 | Variable Volume Combustor - 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 linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner. | 08-07-2014 |
20140216049 | Variable Volume Combustor with Pre-Nozzle Fuel Injection System - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system. | 08-07-2014 |
20140216050 | Variable Volume Combustor with Nested Fuel Manifold System - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system. | 08-07-2014 |
20140216051 | Variable Volume Combustor with an Air Bypass System - The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles. | 08-07-2014 |
20140216054 | Variable Volume Combustor with Aerodynamic Support Struts - 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 providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles. | 08-07-2014 |
20140367495 | FUEL INJECTION NOZZLE AND METHOD OF MANUFACTURING THE SAME - A fuel injection head for use in a fuel injection nozzle comprises a monolithic body portion comprising an upstream face, an opposite downstream face, and a peripheral wall extending therebetween. A plurality of pre-mix tubes are integrally formed with and extend axially through the body portion. Each of the pre-mix tubes comprises an inlet adjacent the upstream face, an outlet adjacent the downstream face, and a channel extending between the inlet and the outlet. Each pre-mix tube also includes at least one fuel injector that at least partially extends outward from an exterior surface of the pre-mix tube, wherein the fuel injector is integrally formed with the pre-mix tube and is configured to facilitate fuel flow between the body portion and the channel. | 12-18-2014 |