Plural Distinct Injectors Patents (Class 60/746)
  • Publication number: 20140331678
    Abstract: A system for distributing compressed air in a combustor of a gas turbine engine. The system may include a flow splitter, a center duct, an outer duct, and an inner duct configured to separate and receive compressed air from a prediffuser exit, and to route separate flows of the compressed air to separate downstream locations for the combustion reaction and for cooling. The system may include an axial mixer configured to axially receive a flow of the compressed air and to direct the flow to mix with fuel provided by an injector.
    Type: Application
    Filed: May 8, 2013
    Publication date: November 13, 2014
    Applicant: Solar Turbines Incorporated
    Inventor: Paul Stuart Cramer
  • Patent number: 8863524
    Abstract: A burner for a gas turbine including a burner housing is provided. Provided is a lean-rich partially premixed low emission burner for a gas turbine combustor providing stable ignition and combustion process at all engine load conditions. At the upstream end of that burner a pilot combustor creates a flow of an unquenched concentration of radicals and heat. Respectively provided is a plurality of quarl sections surrounding the exit of the pilot combustor, a main combustion room defined downstream the pilot combustor and at least a first channel defined as an annular space between an upstream quarl section and the closest downstream quarl section providing air and fuel to a main flame in the combustion room.
    Type: Grant
    Filed: March 26, 2009
    Date of Patent: October 21, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andreas Karlsson, Vladimir Milosavljevic
  • Publication number: 20140290266
    Abstract: A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit. The main fuel pump receives fuel from the boost pump and delivers fuel to a distribution system. The motive fuel pump receives fuel from the boost pump, routes fuel through the storage unit, and delivers fuel to an actuator.
    Type: Application
    Filed: March 27, 2013
    Publication date: October 2, 2014
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Leo J. Veilleux, JR., Gary M. McBrien
  • Publication number: 20140260277
    Abstract: A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.
    Type: Application
    Filed: March 18, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia, Christopher Paul Willis, Ronnie Ray Pentecost
  • Publication number: 20140260305
    Abstract: A combustion chamber may include a first surface and a second surface interconnected by a wall forming a chamber having a central axis. The first surface may define an exhaust opening and the second surface defining a pilot opening, wherein the exhaust opening and the pilot opening align along the central axis. A plurality of inlet ports may be configured to deliver air to the chamber. A plurality of fuel ports may be arranged on an inside of the second surface to deliver fuel to the chamber. The air flow from the inlet ports and fuel from the fuel ports may oppose each other to create a vortex of product proximal to the second surface.
    Type: Application
    Filed: December 30, 2013
    Publication date: September 18, 2014
    Applicant: Rolls-Royce Canada, Ltd.
    Inventors: Joseph L. Hobbs, Jennifer A.M. Sidey, Robert L. Gordon, Epaminondas Mastorakos, Gilles Bourque
  • Publication number: 20140260267
    Abstract: 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.
    Type: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Patrick Benedict Melton, Gregory Allen Boardman, James Harold Westmoreland
  • Publication number: 20140260276
    Abstract: A system includes an end cover for a multi-tube fuel nozzle. The end cover includes a first side, a second side disposed opposite the first side, a plurality of fuel injectors disposed on the first side, and at least one pre-orifice disposed within a passage within the end cover between the first and second sides. The pre-orifice is configured to be removed through the end cover from the second side.
    Type: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: General Electric Company
    Inventors: James Harold Westmoreland, Patrick Benedict Melton
  • Publication number: 20140245741
    Abstract: In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections. Neighbouring vanes are arranged in unequally-shaped pairs in which either: (i) the first vane of each pair exhibits compound lean, and the second vane of the pair exhibits reverse compound lean or has substantially no tangential lean, (ii) the first vane of each pair has substantially no tangential lean, and the second vane of the pair exhibits reverse compound lean, or (iii) the first vane of each pair exhibits reverse compound lean, and the second vane of the pair exhibits greater reverse compound lean. Within each unequally-shaped pair the first vane is on the pressure surface side of the second vane.
    Type: Application
    Filed: February 27, 2014
    Publication date: September 4, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Li HE, Amir RAHIM, Bidur KHANAL, Eduardo ROMERO
  • Publication number: 20140238041
    Abstract: The present application provides a fuel delivery system for a combustor with reduced coherence and/or reduced combustion dynamics. The combustor can assembly may include a first manifold for delivering a first flow of fuel to a first set of fuel injectors and a second manifold for delivering a second flow of fuel to a second set of fuel injectors. The first flow of fuel may have a first temperature and the second flow of fuel may have a second temperature. The first temperature may be higher than the second temperature.
    Type: Application
    Filed: February 27, 2013
    Publication date: August 28, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: SARAH LORI CROTHERS, CHRISTAN XAVIER STEVENSON, DAVID LEACH
  • Patent number: 8800289
    Abstract: 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.
    Type: Grant
    Filed: September 8, 2010
    Date of Patent: August 12, 2014
    Assignee: General Electric Company
    Inventors: Thomas Edward Johnson, Willy Steve Ziminsky, Jonathan Dwight Berry
  • Patent number: 8789374
    Abstract: A combustor for a gas turbine engine having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.
    Type: Grant
    Filed: February 7, 2013
    Date of Patent: July 29, 2014
    Assignee: United Technologies Corporation
    Inventor: James B. Hoke
  • Publication number: 20140202162
    Abstract: Colorless distributed combustion (CDC) reactors or green combustion gas turbine combustors having a combustion chamber are presented for improved performance of gas turbine combustion engines. The combustors are configured and designed for providing a superior pattern factor (uniform thermal field in the combustion zone) and a reduction or complete elimination of pollutants emission from the combustor (i.e., zero emission gas turbine combustor) and uniform thermal field in the entire combustion zone to provide significantly improved pattern factor. Colorless distributed combustion is achieved with fuel and air entering the combustion chamber via one or more injection ports as non-premixed, or premixed. Rectangular, cylindrical, stadium and elliptical shaped combustors are presented with injection ports and exit ports located in various locations of the combustors.
    Type: Application
    Filed: March 24, 2014
    Publication date: July 24, 2014
    Applicant: University of Maryland
    Inventor: Ashwani K. Gupta
  • Publication number: 20140202161
    Abstract: A combustor includes: a combustor basket configured to surround a fuel nozzle from an outer circumferential side, and a plurality of connecting members formed in a circumferential direction at intervals to connect a rear end of the combustor basket and a casing and configured to define a flow path through which compressed air introduced into the combustor basket flows. A circulation direction of the compressed air flowing through the flow path is configured to be reversed at a rear end of the combustor basket and the compressed air is introduced into the fuel nozzle. The flow path is partially or entirely inclined in the circumferential direction to blow the compressed air.
    Type: Application
    Filed: January 22, 2014
    Publication date: July 24, 2014
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Atsushi Yuasa, Toshihiko Saito, Kotaro Miyauchi, Keijiro Saito, Satoshi Takiguchi
  • Publication number: 20140196465
    Abstract: An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.
    Type: Application
    Filed: January 11, 2013
    Publication date: July 17, 2014
    Inventors: Walter R. Laster, Peter Szedlacsek
  • Publication number: 20140190175
    Abstract: A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.
    Type: Application
    Filed: March 10, 2014
    Publication date: July 10, 2014
    Applicant: United Technologies Corporation
    Inventors: Joel H. Wagner, Paul M. Lutjen
  • Publication number: 20140190170
    Abstract: 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.
    Type: Application
    Filed: January 7, 2013
    Publication date: July 10, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jun Cai, Gregory Allen Boardman, Hasan Karim, Lucas John Stoia
  • Patent number: 8769954
    Abstract: A fluid manifold apparatus includes: (a) an array of spaced-apart manifold fittings, each manifold fitting aligned in a predetermined angular orientation. Each manifold fitting includes: (i) a tubular neck; (ii) a pair of spaced-apart tubular arms extending away from a first end of the neck; and (iii) a coupling connected to a second end of the neck; and (b) a plurality of curved tubes, each tube being coupled to one arm of each of two adjacent manifold fittings.
    Type: Grant
    Filed: December 31, 2009
    Date of Patent: July 8, 2014
    Assignee: General Electric Company
    Inventors: Kevin Michael Fiebig, Joshua Brown, Joseph Nath
  • Patent number: 8769956
    Abstract: A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.
    Type: Grant
    Filed: August 30, 2013
    Date of Patent: July 8, 2014
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Kevin Weston McMahan, Carl Robert Barker
  • Patent number: 8763359
    Abstract: A system for a gas turbine engine includes a combustor assembly coupled to a plurality of first nozzles having outlet passageways coupled to a first fuel source and first passageways coupled to a second fuel source. The system also includes the combustor assembly coupled to a second nozzle that has second passageways coupled to the second fuel source. An associated control system, coupled to the combustor assembly, is configured to channel a first fuel from the first fuel source through the outlet passageways, and channel a second fuel from the second fuel source through the second passageways when the engine attains a predetermined load. The control system is further configured to channel the second fuel from the second fuel source through the first passageways and to reduce a flow of the first fuel entering the first nozzles when the engine is at a load greater than a first predetermined load.
    Type: Grant
    Filed: June 27, 2011
    Date of Patent: July 1, 2014
    Assignee: General Electric Company
    Inventor: Carey Edward Romoser
  • Publication number: 20140174096
    Abstract: An arrangement for injection of an emulsion of a first fluid and a second fluid into a flame of a burner has a central gas duct, an outer gas channel disposed coaxially with the gas duct, and a fluid channel disposed coaxially between the gas duct and the outer gas channel The central gas duct and the fluid channel are separated by a first frustoconical wall. The fluid channel and the outer gas channel are separated by a second frustoconical wall. The arrangement is mounted concentrically surrounding a heat source which provides through the gas duct hot gases being directed into the flame of the burner. Further, the arrangement includes a mixing device for forming an emulsion of the first fluid and the second fluid, for supplying the emulsion into the fluid channel and for injecting the emulsion from the fluid channel into the flame.
    Type: Application
    Filed: September 20, 2011
    Publication date: June 26, 2014
    Inventor: Vladimir Dusan Milosavljevic
  • Patent number: 8756934
    Abstract: A combustor generally includes a shroud that that defines at least one inlet passage extends circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port, at least one outlet port and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve may extend through the fuel nozzle passage. The tube, the sleeve, and the first plate may at least partially define an outlet passage. A first fluid flow path generally extends from the at inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.
    Type: Grant
    Filed: October 30, 2012
    Date of Patent: June 24, 2014
    Assignee: General Electric Company
    Inventors: Patrick Benedict Melton, Bryan Wesley Romig, Lucas John Stoia
  • Patent number: 8752386
    Abstract: A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets.
    Type: Grant
    Filed: May 25, 2010
    Date of Patent: June 17, 2014
    Assignees: Siemens Energy, Inc., Mikro Systems, Inc.
    Inventors: Timothy A. Fox, Reinhard Schilp, Domenico Gambacorta
  • Patent number: 8752387
    Abstract: Fuel control arrangements for gas turbine engines generally comprise an injector and a fuel control valve. Typically the fuel control valve is controlled in terms of fuel demand through fuel pressure presented to the valve. Fuel demand may vary and in such circumstances stagnation of fuel adjacent to the valve may cause degradation of the fuel and therefore spurious operational performance. By providing a dedicated working fluid, and typically hydraulic, pressure to the valve a variable aperture port can be displaced to alter the fuel flow configuration within the valve. In such circumstances different fuel valve conditions can be generated by altering the available area of aperture in the port to divert or present fuel to the injector between and across first or primary fuel paths and second or pilot fuel paths as required. Thus more flexibility with regard to fuel presentation to the injector is achieved as well as consistency with respect to avoiding fuel degradation as fuel demand varies.
    Type: Grant
    Filed: May 21, 2009
    Date of Patent: June 17, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Mark Scully
  • Publication number: 20140157781
    Abstract: A gas turbine engine lean burn fuel injector includes a fuel injector head which has a first air swirler, a second air swirler arranged around the first air swirler, a pilot fuel injector arranged radially between the first air swirler and the second air swirler. A third air swirler arranged around the second air swirler, a fourth air swirler arranged around the third air swirler and a main fuel injector arranged radially between the third air swirler and the fourth air swirler. A shroud is arranged around the fourth air swirler. A downstream end of the shroud is generally circular in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head and an upstream end of the shroud is generally elliptical in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head.
    Type: Application
    Filed: November 26, 2013
    Publication date: June 12, 2014
    Applicant: Rolls-Royce PLC
    Inventors: Anthony John MORAN, Christopher Luke FORD, Jonathan Frederick CARROTTE, Alastair Duncan WALKER
  • Patent number: 8745987
    Abstract: A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube extending from the central nozzle to the first side nozzle such that fuel is communicable between the connector, the central nozzle and the first side nozzle and a second leg. The second leg is formed to define a tube extending from the central nozzle to the second side nozzle such that the fuel is communicable between the central nozzle and the second side nozzle.
    Type: Grant
    Filed: October 28, 2010
    Date of Patent: June 10, 2014
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Jonathan Hale Kegley, Crystal McGee McConnaughhay, Bryan Wesley Romig
  • Patent number: 8739543
    Abstract: A method for operating a burner including a burner outlet opening with at least two sectors, each sector is assigned at least one fuel nozzle, is provided. The method is characterized in that fuel is supplied separately to the fuel nozzles of different sectors. Also described is a burner which includes at least two sectors wherein each sector is assigned at least one fuel nozzle. The burner includes at least two separate fuel supply lines and a device for adjusting the fuel mass flow which flows through the respective fuel supply line. The fuel supply lines supply fuel to the fuel nozzles of different sectors. Also described is a gas turbine which is fitted with at least one burner.
    Type: Grant
    Filed: January 18, 2008
    Date of Patent: June 3, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Eberhard Deuker, Anil Gulati, Andreas Heilos
  • Patent number: 8739545
    Abstract: A burner for a gas turbine engine is provided. The burner includes a radial swirler for creating a swirling fuel/air mix, a combustion chamber where combustion of the swirling fuel/air mix occurs, and a pre-chamber located between the radial swirler and the combustion chamber. The radial swirler includes a plurality of vanes arranged in a circle, generally radially inwardly extending flow slots are defined between adjacent vanes in the circle, each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, and a base and top. A flow slot includes a first gas fuel injection hole in its base and a flow slot includes a second gas fuel injection hole in its first side wherein the amounts of gas fuel injected via the first and second gas fuel injection holes are independently variable.
    Type: Grant
    Filed: April 27, 2010
    Date of Patent: June 3, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andrew Cant, Paul Headland, Daniel Leggett
  • Patent number: 8726668
    Abstract: A pilot fuel injector tip includes concentric primary and secondary pilot fuel nozzles having a circular primary exit axially aft and downstream of an annular secondary exit respectively. A fuel nozzle assembly includes a pilot swirler flowpath section having an annular inwardly tapering conical flowpath section surrounding primary and secondary exits. An inwardly tapering conical wall section radially inwardly bounding flowpath section defines a conical surface. Exits are located at or axially forward or upstream of the conical surface. An annular secondary fuel supply passage in secondary pilot fuel nozzle includes a secondary fuel swirler with an array of helical spin slots that may have rectangular cross sections. A chamfered leading edge of an annular wall section disposed between an outer pilot swirler and an inlet to an injector cooling flowpath surrounding the second pilot swirler includes a radially inwardly facing conical chamfered surface for deflecting dirt from cooling flowpath.
    Type: Grant
    Filed: December 17, 2010
    Date of Patent: May 20, 2014
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Michael Anthony Benjamin, Duane Douglas Thomsen, Alfred Albert Mancini
  • Publication number: 20140130477
    Abstract: 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.
    Type: Application
    Filed: November 14, 2012
    Publication date: May 15, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Wei Chen, Abdul Rafey Khan, Derrick Walter Simons
  • Patent number: 8707671
    Abstract: A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.
    Type: Grant
    Filed: July 1, 2009
    Date of Patent: April 29, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Sosuke Nakamura, Satoshi Tanimura, Shinji Akamatsu, Shinsuke Nakamura, Takashi Sonoda, Akihiko Saito, Makoto Kishi
  • Patent number: 8707707
    Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto is combustible, a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power a rotation of the turbine blades, a transition zone, including a second interior in which a second fuel supplied thereto and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are supported by the transition zone and coupled to a fuel circuit, and which are configured to supply the second fuel to the second interior in any one or more of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
    Type: Grant
    Filed: January 7, 2009
    Date of Patent: April 29, 2014
    Assignee: General Electric Company
    Inventors: Krishna Kumar Venkataraman, Jason Charles Terry, Chetan Babu Velkur, Hasan Karim
  • Patent number: 8701379
    Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.
    Type: Grant
    Filed: January 19, 2011
    Date of Patent: April 22, 2014
    Assignee: Aerojet-General Corporation
    Inventor: Melvin J. Bulman
  • Patent number: 8701382
    Abstract: A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
    Type: Grant
    Filed: January 7, 2009
    Date of Patent: April 22, 2014
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Jason Charles Terry
  • Patent number: 8695348
    Abstract: A combustor of the present invention includes: a plurality of nozzles which is arranged around the central axis of a combustor and of which each base end is connected to an oil supply tube; a nozzle tube base which supports the plurality of nozzles and includes an oil chamber supplying fuel to the nozzles via an oil inflow portion provided in each oil supply tube; a first guide portion which faces the center of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion; and a second guide portion which faces the base end of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion.
    Type: Grant
    Filed: October 27, 2010
    Date of Patent: April 15, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Katsuyoshi Omae, Kenta Taniguchi, Yoshitaka Terada, Takashi Onozuka
  • Publication number: 20140096502
    Abstract: A burner for a gas turbine is provided. The burner has a pilot combustor, a supply module providing pilot fuel and air into a pilot combustion room enclosed by a pilot burner housing having a tapered exit throat discharging radicals and heat generated in a pilot combustion zone into a main combustion room. An equalizer has holes for main flow air entering a cavity in a radial direction with regard to a burner axis defined by centers of pilot combustion zone and main combustion zone. A fuel injector is downstream the equalizer to supply flow fuel into flow air. A swirler is downstream the injector to give flow distribution to the flow fuel and air entering the main combustion room. A channel leads from the equalizer to the swirler arranged circumferentially around the pilot burner housing to direct the main air flow from the equalizer in axial and circumferential direction.
    Type: Application
    Filed: September 28, 2011
    Publication date: April 10, 2014
    Inventors: Andreas Karlsson, Vladimir Dusan Milosavljevic, Magnus Persson
  • Patent number: 8689559
    Abstract: An embodiment of the present invention provides a method and system of operating a combustion system that has Lean direct injection (LDI) functionality. The method and system provides a passive cooling system for an injector of the LDI system. The method and system may also provide a means to direct the flow of the fluid exiting the injector of the LDI system.
    Type: Grant
    Filed: March 30, 2009
    Date of Patent: April 8, 2014
    Assignee: General Electric Company
    Inventors: Gilbert O. Kraemer, Jonathan D. Berry, Richard F. Keyser
  • Patent number: 8689562
    Abstract: In one embodiment, alternative combustion cavity layouts are provided for practicing fuel staging in a trapped vortex (TVC) combustion apparatus comprising an inlet premixer, for injecting fuel-air mixture into the inlet of the combustion apparatus and one or more vortex premixers, for injecting fuel-air mixture into the recirculating vortex within each of one or more trapped vortex cavities. A plurality of TVC cavities, may, for example, be laid out axially, radially, peripherally, internally, or in combinations of such arrangements. These layouts may be used in conjunction with a fuel staging method whereby the relative proportion of mixture introduced through the inlet and the respective vortex premixers can be varied as a function of operating conditions.
    Type: Grant
    Filed: November 30, 2009
    Date of Patent: April 8, 2014
    Inventor: Donald W. Kendrick
  • Patent number: 8689561
    Abstract: In one embodiment, a premixer is provided for use, e.g., with trapped vortex (TVC) combustors, that injects premixed fuel and air directly into the recirculating vortex, in a manner compatible with natural vortex flow in the cavity.
    Type: Grant
    Filed: November 30, 2009
    Date of Patent: April 8, 2014
    Inventor: Donald W. Kendrick
  • Publication number: 20140090390
    Abstract: The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture.
    Type: Application
    Filed: September 26, 2013
    Publication date: April 3, 2014
    Inventors: PETER JOHN STUTTAFORD, STEPHEN JORGENSEN, TIMOTHY HUI, YAN CHEN, HANY RIZKALLA, KHALID OUMEJJOUD
  • Publication number: 20140083105
    Abstract: An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to surround the pilot nozzle unit (12) for spraying a fuel for premix combustion, and a flow guide (27) disposed on a downstream side of each of the fuel nozzle assemblies (10) and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (10), which gradually increase in a downstream direction.
    Type: Application
    Filed: November 27, 2013
    Publication date: March 27, 2014
    Applicants: Japan Aerospace Exploration Agency, Kawasaki Jukogyo Kabushiki Kaisha
    Inventors: Masayoshi KOBAYASHI, Takeo ODA, Ryusuke MATSUYAMA, Atsushi HORIKAWA, Hitoshi FUJIWARA
  • Patent number: 8667800
    Abstract: A flameless burner for a gas turbine engine includes a burner body having a longitudinal axis, an upstream section and a downstream section. The upstream section of the burner body defines a primary swirl generating chamber having air swirlers associated therewith. The primary swirl generating chamber is adapted and configured to receive compressor discharge air through the air swirlers. The strong swirl of the compressor discharge air forms a recirculation zone that entrains combustion product gases toward the burner body. Fuel injectors are operatively connected to the downstream section of the burner body for issuing fuel into the recirculated combustion product gases.
    Type: Grant
    Filed: May 13, 2009
    Date of Patent: March 11, 2014
    Assignee: Delavan Inc.
    Inventors: Michael D. Cornwell, Nicholas R. Overman, Ephraim Gutmark
  • Publication number: 20140060063
    Abstract: 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.
    Type: Application
    Filed: September 6, 2012
    Publication date: March 6, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Gregory Allen Boardman, Ronald James Chila, Mark Allan Hadley, Johnie Franklin McConnaughhay, Sarah Lori Crothers
  • Patent number: 8661825
    Abstract: A unitary fuel injection manifold for a secondary fuel nozzle improves fuel-air mixing and offers flexibility to alter the mixing profile through adaptability to a variety of number, types, and orientation of discharge outlets to the combustion air mixing space around the secondary fuel nozzle. An aerodynamic surface with reduced extension into the mixing space reduces pressures drop and interference with design airflow. Manifold integrity is enhanced by elimination of fillet welds to mount external pegs.
    Type: Grant
    Filed: December 17, 2010
    Date of Patent: March 4, 2014
    Assignee: General Electric Company
    Inventors: Divyang Rajendra Desai, Sandeep Gopalakrishna, Kodukulla Venkat Sridhar, Amit Monga
  • Patent number: 8661824
    Abstract: An airblast fuel nozzle assembly (10) comprising a sleeve structure having a series of coaxial sleeves forming an inner-air circuit, an outer-air circuit, a main-fuel-feed circuit, and a pilot-fuel-feed circuit. The pilot-fuel-feed circuit includes a channel (44), and a discharge region (45) with exits (46). The exits (46) have a combined cross-sectional area that is substantially less than the cross-sectional area of the channel (44) upstream of the discharge region (45). In this manner, the pilot-fuel-feed circuit itself can provide a relatively large pressure drop across the channel region (44), and thereby assist in self atomization during ignition stages of engine operation.
    Type: Grant
    Filed: May 26, 2010
    Date of Patent: March 4, 2014
    Assignee: Parker-Hannifin Corporation
    Inventors: Robert R. Pelletier, Michael K. Teter
  • Patent number: 8656721
    Abstract: This invention provides a gas turbine combustor including: a main burner at a head portion of a combustor cylinder; and a pre-mixing type supplemental burner at a downstream portion of the combustor cylinder and extending through a circumferential wall thereof. The supplemental burner includes: an introducing passage configured to deflect a part of the compressed air radially inward, the compressed air flowing from an air passage between the circumferential wall of the combustor cylinder and a housing surrounding the circumferential wall toward the head portion of the combustor cylinder, and introduce the compressed air into the combustor cylinder; and a fuel nozzle configured to supply the fuel from fuel injection holes to the compressed air introduced into the introducing passage to produce a pre-mixed gas in the introducing passage.
    Type: Grant
    Filed: March 11, 2010
    Date of Patent: February 25, 2014
    Assignee: Kawasaki Jukogyo Kabushiki Kaisha
    Inventors: Kiyoshi Matsumoto, Takeo Oda
  • Patent number: 8650881
    Abstract: A method for controlling a gas turbine combustion system includes supplying an ultra low calorific fuel to a combustor of the combustion system through a first fuel circuit, controlling a supply of the ultra low calorific fuel through a second fuel circuit as required to control the volumetric flow of the ultra low calorific fuel through the combustor, and combusting the ultra low calorific fuel in the combustor.
    Type: Grant
    Filed: June 30, 2009
    Date of Patent: February 18, 2014
    Assignee: General Electric Company
    Inventors: Willy Steve Ziminsky, Lewis Berkley Davis, Jr.
  • Patent number: 8646275
    Abstract: A gas-turbine lean combustor includes a combustion chamber (2) and a fuel nozzle (1) which includes a pilot fuel injection (17) and a main fuel injection (18). The main fuel injection (18) includes central recesses (23) for a controlled inhomogeneous fuel injection, the number of said recesses on the circumference ranging from 8 to 40 and said recesses having an angle of inclination ?2 in circumferential direction of 10°??2?60° and an axial angle of inclination ?1 relative to the combustor axis (4) between ?10°??1?90°.
    Type: Grant
    Filed: March 8, 2012
    Date of Patent: February 11, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Leif Rackwitz, Imon-Kalyan Bagchi, Thomas Doerr
  • Publication number: 20140033719
    Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles and a combustion zone downstream of the fuel nozzles. The combustion zone may include a number of steps such that the combustion zone expands in a radial direction downstream of the fuel nozzles.
    Type: Application
    Filed: August 2, 2012
    Publication date: February 6, 2014
    Inventors: Rahul Ravindra Kulkarni, Shreenivansan Obla Jayaprakash
  • Patent number: 8640463
    Abstract: A swirler for fuel injection in a gas turbine engine includes a frustoconical swirler body. A first and a second air flow path direct air in generally opposed circumferential directions into the swirler. These air paths intermix and create turbulence. As this turbulence encounters fuel droplets, the fuel is atomized, and uniformly distributed within the air flow. A shear layer is created adjacent an inner surface of the swirler body. In a separate feature, a third air flow path is directed into the air.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: February 4, 2014
    Assignee: United Technologies Corporation
    Inventor: Albert K. Cheung
  • Publication number: 20140026586
    Abstract: The invention refers to a reheat burner that includes a flow channel for a hot gas flow with a lance arranged along said flow channel, protruding into the flow channel for injecting a fuel over an injection plane perpendicular to a channel longitudinal axis, wherein the channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas flow direction. The mixing zone provides at least one axially region having different cross sectional areas along its longitudinal axis with continuously changing shape, or having non circular cross section areas which change location along its longitudinal axis by continuously rotation around the longitudinal axis.
    Type: Application
    Filed: July 26, 2013
    Publication date: January 30, 2014
    Applicant: ALSTOM Technology Ltd
    Inventor: Michael Düsing