With Fuel Injector Patents (Class 60/740)
Fuel control valve integral with injector (Class 60/741)
Unitary injector having plural fuel flow paths (Class 60/742)
Surface film injector (Class 60/743)
Rotary fuel injector (Class 60/744)
Plural distinct injectors (Class 60/746)
With attendant coaxial air swirler (Class 60/748)
  • FUEL NOZZLE AND METHOD OF REPAIR
    Publication number: 20130139513
    Abstract: A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body.
    Type: Application
    Filed: January 30, 2013
    Publication date: June 6, 2013
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Pratt & Whitney Canada Corp.
  • LEAF SPRING DAMPER FOR A TURBINE ENGINE FUEL DELIVERY SYSTEM
    Publication number: 20130139512
    Abstract: A turbine engine fuel delivery system includes a mounting platform, a spray bar assembly and a leaf spring damper with a stack of a plurality of leaf springs. The stack includes a base segment connected longitudinally between a first spray bar contact segment and a second spray bar contact segment. The base segment is connected to the mounting platform and is located a first distance from the spray bar assembly. The first spray bar contact segment engages the spray bar assembly and is located a second distance from the mounting platform. The second spray bar contact segment engages the spray bar assembly and is located a third distance from the mounting platform.
    Type: Application
    Filed: December 6, 2011
    Publication date: June 6, 2013
    Applicant: United Technologies Corporation
    Inventors: Andreas Sadil, Marc J. Muldoon, Bessem Jlidi
  • Coannular oil injection nozzle
    Patent number: 8453454
    Abstract: 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.
    Type: Grant
    Filed: April 14, 2010
    Date of Patent: June 4, 2013
    Assignee: General Electric Company
    Inventors: Benjamin Paul Lacy, Thomas Edward Johnson, William David York, Baifang Zuo
  • Flexible combustor fuel nozzle
    Patent number: 8448442
    Abstract: The present application provides a flexible combustor fuel nozzle. The flexible combustor fuel nozzle may include a main passage in communication with a source of natural gas and a source of low BTU fuel, a secondary passage surrounding the main passage and in communication with the source of low BTU fuel and a source of purge air, and a tertiary passage surrounding the secondary passage and in communication with the source of low BTU fuel, the source of purge air, and a source of diluent.
    Type: Grant
    Filed: May 19, 2011
    Date of Patent: May 28, 2013
    Assignee: General Electric Company
    Inventors: Ilya Aleksandrovich Slobodyanskiy, Joel Hall, Jesse Barton, Vijaykant Sadasivuni
  • Fuel injector mounting system
    Patent number: 8448449
    Abstract: A system is provided for mounting fuel injectors to a gas turbine engine. The system comprises an engine casing having a plurality of apertures formed therein. The system further comprises a plurality of first and second fuel injectors. Each fuel injector has a respective flange for mounting the fuel injector to the casing at a respective aperture so that the fuel injector extends into the engine. The first fuel injectors have flanges which are dismountably sealed to an inner side of the casing. The second fuel injectors have flanges which are dismountably sealed to an outer side of the casing. The flanges of the first fuel injectors are configured to allow them to pass through the apertures of the second fuel injectors. A first fuel injector can be dismounted from the casing and withdrawn therefrom through the aperture of a dismounted second fuel injector.
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: May 28, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Michael L. Carlisle
  • GAS TURBINE COMBUSTION CHAMBER
    Publication number: 20130125550
    Abstract: A gas turbine combustion chamber is provided including a pilot fuel nozzle arranged in the central section of a cylinder that opens at one end towards a combustion chamber. The pilot fuel nozzle includes a fuel nozzle and a cylindrical outer casing around the outer circumference of the fuel nozzle. A pilot swirl element is arranged between fuel nozzle and outer casing, including a plurality of main burners which are arranged around the pilot fuel nozzle, and including a pilot cone having an inner side and an outer side. The pilot cone is arranged on the pilot fuel nozzle and an opening, such that a pilot flame is formed in the pilot cone by mixing air and pilot fuel in order to ignite a fuel injected by the main burners, wherein the pilot cone has turbulence generators on the inner side and/or outer side thereof.
    Type: Application
    Filed: June 15, 2011
    Publication date: May 23, 2013
    Inventor: Bernd Prade
  • Coaxial fuel and air premixer for a gas turbine combustor
    Patent number: 8443607
    Abstract: An air/fuel premixer comprising a peripheral wall defining a mixing chamber, a nozzle disposed at least partially within the peripheral wall comprising an outer annular wall spaced from the peripheral wall so as to define an outer air passage between the peripheral wall and the outer annular wall, an inner annular wall disposed at least partially within and spaced from the outer annular wall, so as to define an inner air passage, and at least one fuel gas annulus between the outer annular wall and the inner annular wall, the at least one fuel gas annulus defining at least one fuel gas passage, at least one air inlet for introducing air through the inner air passage and the outer air passage to the mixing chamber, and at least one fuel inlet for injecting fuel through the fuel gas passage to the mixing chamber to form an air/fuel mixture.
    Type: Grant
    Filed: February 20, 2009
    Date of Patent: May 21, 2013
    Assignee: General Electric Company
    Inventors: William D. York, Willy S. Ziminsky, Benjamin P. Lacy
  • Feed arm for a multiple circuit fuel injector
    Patent number: 8443608
    Abstract: A feed arm for a multiple circuit fuel injector of a gas turbine engine. The feed arm includes an elongated tubular sleeve having a central bore with an interior wall defining an inner diameter, and an elongated fuel tube positioned within the bore of the tubular sleeve. The fuel tube includes a tubular wall defining an outer diameter, which is substantially equal to the inner diameter of the central bore. A primary fuel flow passage is formed within the tubular wall of the fuel tube and bounded by the interior wall of the tubular sleeve, and the primary fuel flow passage circumferentially extends around the fuel tube at least once along the axial length of the fuel tube. A secondary fuel flow passage extends through a central portion of the fuel tube, and the fuel tube is configured to facilitate heat transfer by conduction and/or convection.
    Type: Grant
    Filed: February 26, 2008
    Date of Patent: May 21, 2013
    Assignee: Delavan Inc
    Inventor: Brandon Phillip Williams
  • Gas-turbine burner for a gas turbine with purging mechanism for a fuel nozzle
    Patent number: 8443609
    Abstract: A gas-turbine burner for a gas turbine includes a fuel nozzle 1 having several fuel exit holes 23, which are each connected to a fuel line 5, 7, 29, 30, through which fuel can be passed selectively Between individual fuel exit holes 23, different static pressures of the airflow are provided between fuel lines flown by fuel and fuel lines not flown by fuel.
    Type: Grant
    Filed: March 18, 2009
    Date of Patent: May 21, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thomas Doerr, Leif Rackwitz, Waldemar Lazik
  • FUEL INJECTION SYSTEM FOR TURBOJET ENGINE AND METHOD OF ASSEMBLING SUCH AN INJECTION SYSTEM
    Publication number: 20130118177
    Abstract: A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion.
    Type: Application
    Filed: July 18, 2011
    Publication date: May 16, 2013
    Applicant: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario César De Sousa, Guillaume Sevi, Brice Arnaud Demoulin
  • COMBUSTOR ASSEMBLY FOR A GAS TURBOMACHINE
    Publication number: 20130111918
    Abstract: A turbomachine combustor assembly includes a combustor housing, a first combustion zone arranged in the combustor housing, a second combustion zone arranged downstream from the first combustion zone, and one or more injector assemblies positioned downstream from the first combustion zone and upstream from the second combustion zone. The one or more injector assemblies includes a first injector member having a first centerline axis and a second injector member having a second centerline axis. The second injector member extends though the first injector member with the second centerline axis being off-set from the first centerline axis.
    Type: Application
    Filed: November 7, 2011
    Publication date: May 9, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Atanu Kumar Kundu, Karim Hasan, Arjun Singh, Krishna Kumar Venkataraman
  • BURNER ASSEMBLY
    Publication number: 20130104554
    Abstract: A burner assembly for a gas turbine is provided. The burner assembly has a combustor, a centrally arranged pilot burner and plurality of main burners surrounding the pilot burner. Each main burner has a cylindrical housing having a lance which is centrally arranged therein and has a fuel channel for liquid fuel. The lance is supported on the housing by swirl blades and an attachment is arranged on the lance in the direction of the combustor. The liquid fuel nozzle is arranged in the attachment downstream of the swirl blades and connected to the fuel channel. For the improved mixing of the fuel with the air, the liquid fuel nozzle is designed as a full jet nozzle and the full jet nozzle has a length and a diameter, the ratio of the length to the diameter is at least 1.5.
    Type: Application
    Filed: July 1, 2011
    Publication date: May 2, 2013
    Inventors: Siegfried Bode, Timothy A. Fox, Thomas Grieb, Matthias Hase, Jürgen Meisl, Sebastian Pfadler
  • INJECTION APPARATUS
    Publication number: 20130104553
    Abstract: An injection apparatus is provided and includes an annular base defining an injection hole location and having a protrusion about the injection hole location and a tubular body formed to define an injection hole, the tubular body to be sealably fastened to the annular base and the protrusion at the injection hole location such that the tubular body and the protrusion cooperatively define a plenum such that the plenum is communicative with the injection hole.
    Type: Application
    Filed: November 1, 2011
    Publication date: May 2, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Lucas John Stoia, Patrick Benedict Melton
  • Injector having multiple fuel pegs
    Patent number: 8429915
    Abstract: A fuel injector is provided, including a fuel injector body, a plurality of fuel vanes, and a plurality of fuel pegs. The injector body includes a manifold and an inlet. The manifold is configured for receiving fuel, and the inlet is configured for receiving air. The fuel vanes are located within the injector body and are positioned in a direction that is generally parallel with a longitudinal axis of the injector body to orient the air flowing from the inlet. The plurality of fuel pegs are fluidly connected to the manifold and are arranged within the plurality of fuel vanes. The plurality of fuel pegs are each spaced at a distance that is about equal between each of the plurality of fuel pegs.
    Type: Grant
    Filed: October 17, 2011
    Date of Patent: April 30, 2013
    Assignee: General Electric Company
    Inventors: Mark Allan Hadley, David Kenton Felling
  • DIFFUSION NOZZLES FOR LOW-OXYGEN FUEL NOZZLE ASSEMBLY AND METHOD
    Publication number: 20130098048
    Abstract: A fuel nozzle assembly has been conceived for a combustor in a gas turbine including a first passage and fourth passage connectable to a source of gaseous fuel, a second passage connectable to a source of a gaseous oxidizer, and a third passage coupled to a source of a diluent gas, wherein the first passage is a center passage and is configured to discharge gaseous fuel from nozzles at a discharge end of the center passage, the second passage is configured to discharge the gaseous oxidizer through nozzles adjacent to the nozzles for the center passage, the third passage discharges a diluent gas through nozzles adjacent to the nozzles for the second passage, and the fourth passage is configured to discharges the gaseous fuel downstream of the discharge location for the first, second and third passages.
    Type: Application
    Filed: October 21, 2011
    Publication date: April 25, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Predrag POPOVIC, Abinash BARUAH
  • Hydrajetting Nozzle and Method
    Publication number: 20130098043
    Abstract: A jetting device comprises a body, and an interior flow path within the body. The interior flow path comprises a flow section, an expansion section, and a shoulder formed at the intersection of the flow section and the expansion section. The length and diameter of the expansion section are configured to allow a portion of the pressure of the fluid downstream of the expansion section to provide power to a fluid flowing through the nozzle when the fluid is flowing through the nozzle.
    Type: Application
    Filed: December 12, 2012
    Publication date: April 25, 2013
    Applicant: HALLIBURTON ENERGY SERVICES, INC.
    Inventor: HALLIBURTON ENERGY SERVICES, INC.
  • FLASHBACK RESISTANT TUBES IN TUBE LLI DESIGN
    Publication number: 20130098044
    Abstract: A late lean fuel injection nozzle for a gas turbine includes a first outer air supply tube having a relatively large inner diameter and an outlet at a distal end thereof. The first outer air supply tube is adapted to supply air to a combustion chamber, and at least one fuel injection tube having a relatively smaller diameter enters a distal end portion of the first outer air supply tube and extends within the first outer air supply tube substantially to the outlet.
    Type: Application
    Filed: October 19, 2011
    Publication date: April 25, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Arjun SINGH
  • Fuel nozzle cup seal
    Patent number: 8413447
    Abstract: The present application provides a fuel nozzle assembly. The fuel nozzle assembly may include an end cap assembly, a number of fuel nozzles positioned within the end cap assembly, and one or more cup seals. The cup seals may be positioned between the end cap assembly and the fuel nozzles.
    Type: Grant
    Filed: September 16, 2009
    Date of Patent: April 9, 2013
    Assignee: General Electric Company
    Inventor: David Cihlar
  • FORWARD CASING WITH A CIRCUMFERENTIAL SLOPED SURFACE AND A COMBUSTOR ASSEMBLY INCLUDING SAME
    Publication number: 20130081397
    Abstract: A forward casing used in a combustor assembly for a turbine engine includes a circumferential sloped surface which reduces the total interior volume within the forward casing. The circumferential sloped surface can be flat or concave shaped.
    Type: Application
    Filed: October 4, 2011
    Publication date: April 4, 2013
    Inventor: Brandon Taylor Overby
  • SYSTEM FOR SUPPLYING PRESSURIZED FLUID TO A CAP ASSEMBLY OF A GAS TURBINE COMBUSTOR
    Publication number: 20130074503
    Abstract: A system for supplying pressurized fluid to a combustor of a gas turbine is disclosed. The system may include an end cover and a fuel nozzle extending from the end cover. The fuel nozzle may include a downstream end. Additionally, the system may include a cap assembly configured to receive at least a portion of the fuel nozzle. The cap assembly may include an upstream wall spaced apart from the downstream end, a downstream wall disposed proximate to the downstream end and a cap chamber defined between the upstream and downstream walls. Moreover, a conduit may extend through the end cover and the upstream wall such that a discharge end of the conduit is in flow communication with the cap chamber.
    Type: Application
    Filed: September 28, 2011
    Publication date: March 28, 2013
    Applicant: General Electric Company
    Inventors: Robert Joseph Rohrssen, Patrick Benedict Melton
  • Reheat burner injection system
    Patent number: 8402768
    Abstract: The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions.
    Type: Grant
    Filed: May 7, 2012
    Date of Patent: March 26, 2013
    Assignee: Alstom Technology Ltd.
    Inventors: Khawar Syed, Madhavan Poyyapakkam, Anton Winkler, Andre Theuer
  • SYSTEM AND METHOD FOR CONTROLLING COMBUSTION INSTABILITIES IN GAS TURBINE SYSTEMS
    Publication number: 20130067927
    Abstract: A gas turbine system and a method for controlling combustion instability in a combustion section of a gas turbine system are disclosed. The gas turbine system includes a compressor section, a turbine section connected to the compressor section, and a combustor section connected to the compressor section and the turbine section. The combustor section includes a plurality of combustors. The combustor section further includes at least one igniter for igniting a fuel-air mixture within each of the plurality of combustors into a hot gas. The gas turbine system further includes a control system for controlling a velocity of the hot gas in at least one of the plurality of combustors by controlling an operating parameter of the fuel-air mixture.
    Type: Application
    Filed: September 16, 2011
    Publication date: March 21, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Joseph Kirzhner, Roy Marshall Washam
  • TURNING GUIDE FOR COMBUSTION FUEL NOZZLE IN GAS TURBINE AND METHOD TO TURN FUEL FLOW ENTERING COMBUSTION CHAMBER
    Publication number: 20130061594
    Abstract: A fuel nozzle assembly for a gas turbine, the assembly including: a cylindrical center body; a cylindrical shroud coaxial with and extending around the center body, and a turning guide having an downstream edge extending in a passage between the center body and an inlet to the shroud, wherein the turning guide extends only partially around the center body.
    Type: Application
    Filed: September 9, 2011
    Publication date: March 14, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Jason Thurman Stewart
  • Swozzle design for gas turbine combustor
    Patent number: 8393157
    Abstract: Disclosed is a fuel nozzle for a combustor of a gas turbine engine includes a nozzle inlet, a combustion area and a swirler disposed between the nozzle inlet and combustion area. The swirler includes a plurality of swirler vanes, each swirler vane capable of creating a pressure difference in fluid flow through the swirler between a pressure side and suction side of the swirler vane. The swirler further includes at least one through airflow hole located in at least one swirler vane of the plurality of swirler vanes. The at least one through airflow hole is capable of utilizing the pressure difference between the pressure side and suction side to promote fluid flow through the at least one airflow hole. Also disclosed is a method for operating a combustor.
    Type: Grant
    Filed: January 18, 2008
    Date of Patent: March 12, 2013
    Assignee: General Electric Company
    Inventor: Constantin Dinu
  • Gas turbine fuel injector with insulating air shroud
    Patent number: 8393155
    Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing extending from a first end to a second end along a longitudinal axis. The second end of the housing is fluidly coupled to a combustor of the turbine engine and the housing includes a liquid fuel gallery annularly disposed about the longitudinal axis. The fuel injector also includes a stem extending longitudinally from the first end of the housing to a third end. The stem includes a liquid tube configured to deliver liquid fuel to the fuel injector. The fuel injector also includes an annular shell extending along the longitudinal axis from the first end to the third end and circumferentially disposed about the stem. The fuel injector further includes an insulating air shroud formed inside the shell. The air shroud includes a layer of air between the shell and the stem.
    Type: Grant
    Filed: November 28, 2007
    Date of Patent: March 12, 2013
    Assignee: Solar Turbines Incorporated
    Inventors: James Scott Piper, Hongyu Wang
  • Variable performance valve of a fuel nozzle for a turbine engine
    Patent number: 8393156
    Abstract: A variable performance valve for use in a fuel nozzle is presented. The valve includes a spring, an inner spool having a port, an outer sleeve, and an orifice, which in a fuel nozzle application may be a calibration orifice. In a low flow condition, the inlet to downstream pressure is the spring force divided by the area on which the pressure acts. At low flow the orifice does not cause any appreciable pressure drop. As the flow increases, a pressure drop develops across the orifice. Since the pressure drop across the valve cannot be greater than the spring force divided by valve area, the valve is forced to open to compensate. As flow is increased, the valve will stroke completely open and the pressure drop at the port becomes negligible and the pressure drop across the orifice is nearly 100% of the pressure drop across the valve.
    Type: Grant
    Filed: November 9, 2009
    Date of Patent: March 12, 2013
    Assignee: Woodward, Inc.
    Inventors: Nathan Niemeyer, Charlie Carson
  • FUEL SUPPLY DEVICE OF GAS TURBINE ENGINE
    Publication number: 20130055719
    Abstract: In a fuel supply device of a gas turbine engine of the present invention, a fuel divider 66 includes a fuel entrance E1 into which the fuel supplied from a collecting fuel passage 63 is introduced; a pilot port 76 connected to the pilot fuel passage 64; a main port 77 connected to the main fuel passage 65; a pilot port needle valve element 101 which adjusts an opening degree of the pilot port 76; a main port needle valve element 102 which opens and closes the main port 77; and a drive element 100 which is actuated according to the fuel pressure at the fuel inlet E1 to drive the pilot port needle valve element 101 and the main port needle valve element 102.
    Type: Application
    Filed: March 23, 2011
    Publication date: March 7, 2013
    Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Hideki Ogata, Kazuhiko Ohyama, Tomoyuki Hatano, Akihiro Shimizu, Touya Miwa
  • Gas turbine combustor having counterflow injection mechanism
    Patent number: 8387390
    Abstract: In accordance with certain embodiments, a system includes a counterflow injection mechanism. The counterflow injection mechanism includes a fuel-air injection mechanism having fuel and air passages leading to fuel and air injection openings, wherein the fuel and air injection openings are disposed at an off-center position and a generally counterflow direction relative to a generally lengthwise flow axis of a gas turbine combustor.
    Type: Grant
    Filed: January 3, 2006
    Date of Patent: March 5, 2013
    Assignee: General Electric Company
    Inventor: Joel Meier Haynes
  • Aerodynamically enhanced fuel nozzle
    Patent number: 8387391
    Abstract: A gas turbine engine fuel nozzle assembly includes a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer. A cross over arm extends across inlet to tip. Arm includes an arm fairing surrounding at least one fuel transfer tube to tip. A pilot nose cap is at an upstream end of tip. At least one of the cross over arm and the pilot nose cap includes a rounded forebody followed by a straight afterbody. Rounded forebody of pilot nose cap includes a substantially rounded dome extending forwardly from a rounded nose base and straight afterbody includes a substantially cylindrical nose afterbody parallel to a pilot nose centerline normal to nose base. An arm fairing surrounding fuel transfer tubes to tip includes rounded leading and trailing edges and a rectangular middle section therebetween having flat first and second sides.
    Type: Grant
    Filed: December 17, 2010
    Date of Patent: March 5, 2013
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Michael Anthony Benjamin, Duane Douglas Thomsen, Alfred Albert Mancini
  • Flashback resistant fuel injection system
    Patent number: 8387393
    Abstract: A fuel injector assembly includes a fuel injector that provides fuel to be mixed with air for ignition in a combustor. The fuel injector assembly includes a fuel shroud and a plurality of spanning members. The spanning members are spaced circumferentially on the fuel shroud between the fuel shroud and a base plate assembly, which supports the fuel injector assembly within the combustor. The spanning members space the fuel shroud from the base plate assembly such that an annular gap is formed therebetween. The gap permits a flow of purge air therethrough to be mixed with compressed air entering the fuel shroud and with fuel provided by the fuel injector. The spanning members comprise elongate members having upstream ends that are circumferentially offset from opposed downstream ends so that the spanning members provide tangential velocity to the purge air flowing through the annular gap.
    Type: Grant
    Filed: June 23, 2009
    Date of Patent: March 5, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Kyle L. Landry, Reinhard Schilp
  • Systems and methods of providing high pressure air to a head end of a combustor
    Patent number: 8381526
    Abstract: A combustor includes a first flow path and a second flow path. The first flow path places a diffuser in indirect fluid communication with a combustor cap assembly by way of an intervening lower combustor annular passageway. The second flow path places the diffuser in direct fluid communication with the combustor cap assembly.
    Type: Grant
    Filed: February 15, 2010
    Date of Patent: February 26, 2013
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Constantin Dinu, Carl Robert Barker, Krishna Kumar Venkataraman
  • SYSTEM FOR GASIFICATION FUEL INJECTION
    Publication number: 20130040255
    Abstract: A system includes a gasification fuel injector, which includes a first fuel conduit configured to inject a first fuel flow from a first fuel tip, a second fuel conduit configured to inject a second fuel flow from a second fuel tip, a first gas conduit configured to inject a first gas flow from a first gas tip, a second gas conduit configured to inject a second gas flow from a second gas tip, and a third gas conduit configured to inject a third gas flow from a third gas tip. At least one of the first fuel tip, the second fuel tip, the first gas tip, the second gas tip, or the third gas tip is recessed a distance away from an outlet of the gasification fuel injector. The first and second fuel conduits and the first, second, and third gas conduits are coaxial with one another.
    Type: Application
    Filed: August 10, 2011
    Publication date: February 14, 2013
    Applicant: General Electric Company
    Inventors: Shaoping Shi, Constantin Dinu, Shashishekara Sitharamarao Talya
  • MULTI-FUEL INJECTION NOZZLE
    Publication number: 20130036740
    Abstract: A multi-fuel nozzle (90) for a gas turbine engine. The nozzle includes: an annular main body (68) having a plurality of fuel gas channels (22), all disposed circumferentially about a main body longitudinal axis (14); an annular fuel oil body (30) disposed within the annular main body (68) and having a central oil channel (36) coaxial with the main body longitudinal axis (14); an annular cooling air channel (42) between the annular main body (68) and the fuel oil body (30); a discrete cooling air body (70, 100) having a guide (74, 104), the guide (74, 104) supported independent of a downstream end (84) of the main body (68) and configured to direct cooling air traveling downstream in the annular cooling air channel (42) radially inward at a location immediately downstream of a central oil channel downstream end (34).
    Type: Application
    Filed: August 9, 2011
    Publication date: February 14, 2013
    Inventors: Ulrich Woerz, Jianfan Wu
  • Gas turbine combustor
    Patent number: 8371126
    Abstract: In a gas turbine combustor, a cavity with which a plurality of first air passages communicates is formed by covering with a cover a concave portion of a top hat main body in which the first air passages are formed along the circumferential direction of the top hat main body, a plurality of second fuel passages that communicates with the first fuel passages are formed by connecting an inner ring and an outer ring to the top hat main body and by connecting the inner ring and the outer ring to each other, a peg is fixed on the inner ring to communicate with the second fuel passage through a third air passage, and thin wall portions that serve as a thermal elongation absorbing unit by which thermal elongation is absorbed are provided on the inner ring and the outer ring.
    Type: Grant
    Filed: April 11, 2008
    Date of Patent: February 12, 2013
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Tomoto Nagai, Eigo Katou, Tetsu Konishi
  • FUEL INJECTING ASSEMBLY FOR GAS TURBINE ENGINE
    Publication number: 20130031907
    Abstract: A fuel injecting assembly for a combustor of a gas turbine engine has a gas supply structure, steam supply structure and oil fuel nozzle that are substantially separated to allow relative movement between a respective end section, end portion and end part due to thermal expansion and contraction.
    Type: Application
    Filed: August 2, 2011
    Publication date: February 7, 2013
    Inventors: Ulrich Woerz, Jianfan Wu
  • Gas turbine combustor having a fuel nozzle for flame anchoring
    Patent number: 8365534
    Abstract: A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis. The oxidizer passages are configured for having oxidizer exit the oxidizer passages. The oxidizer passages are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis. The plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor.
    Type: Grant
    Filed: March 15, 2011
    Date of Patent: February 5, 2013
    Assignee: General Electric Company
    Inventors: Predrag Popovic, Abinash Baruah, Gilbert Otto Kraemer, William Thomas Ross
  • Fuel nozzle with multiple fuel passages within a radial swirler
    Patent number: 8365535
    Abstract: A fuel nozzle manifold comprising a flange, a stem and a swirler is provided. The flange has a first fluid inlet fluidly connected to a radially extending first flow passage, the stem includes at least a first axially extending and only partially circumferentially extending flow channel, and the swirler has at least a first radially extending premix passage. The flange and the stem can comprise a homogeneous component, or two separate components fluidly connecting the first axially extending flow channel to the first flow passage, to form a fluid connection between the flange and the stem, the swirler comprises another component fitted together with the flange and stem component and fluidly connecting the first premix passage and the first flow channel.
    Type: Grant
    Filed: February 9, 2009
    Date of Patent: February 5, 2013
    Assignee: General Electric Company
    Inventors: Stanley Kevin Widener, Scott Robert Simmons
  • SYSTEM FOR CONDITIONING AIR FLOW INTO A MULTI-NOZZLE ASSEMBLY
    Publication number: 20130025285
    Abstract: A system includes a turbine fuel nozzle assembly. The turbine fuel nozzle assembly includes a first fuel nozzle including a first air inlet and a second fuel nozzle including a second air inlet. The turbine fuel nozzle assembly also includes a first inlet flow conditioner disposed adjacent the first air inlet of the first fuel nozzle, wherein the first air inlet flow conditioner extends only partially around the first fuel nozzle. The turbine fuel nozzle further includes a second inlet flow conditioner disposed adjacent the second air inlet of the second fuel nozzle, wherein the second air inlet flow conditioner extends only partially around the second fuel nozzle, and the second inlet flow conditioner is separate from the first inlet flow conditioner.
    Type: Application
    Filed: July 29, 2011
    Publication date: January 31, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jason Thurman Stewart, Jonathan Dwight Berry
  • Fuel injector sans support/stem
    Patent number: 8353163
    Abstract: A fuel nozzle is provided. The fuel nozzle includes a heat shield, a fuel tube and a plurality of support members. The support members are radially interposed between the heat shield and the fuel tube. The support members are preferably cylindrical tubes, thus creating voids or pockets between the heat shield and the fuel tube. The cylindrical tubes are connected to one another at a first end are free at an opposed end. As such, the tubes can move or slide relative to one another. Further, the tubes preferably only contact one another with at most line contacts. The fuel nozzle may also include a tip portion that includes a tip heat shield that extends radially outward from the primary heat shield. The tip heat shield defines a cavity that connects with the central cavity of the heat shield. The fuel tube extends through the tip heat shield.
    Type: Grant
    Filed: November 22, 2011
    Date of Patent: January 15, 2013
    Assignee: Woodward, Inc.
    Inventor: David S. Smith
  • Fuel nozzle to withstand a flameholding incident
    Patent number: 8353150
    Abstract: A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone.
    Type: Grant
    Filed: June 7, 2012
    Date of Patent: January 15, 2013
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Stanley Kevin Widener, John Wilbur
  • APPARATUS AND SYSTEMS RELATING TO FUEL INJECTORS AND FUEL PASSAGES IN GAS TURBINE ENGINES
    Publication number: 20130008169
    Abstract: A combustor casing fuel injector in a combustor of a combustion turbine engine, the combustor including a combustor casing that encloses internal structure of the combustor, wherein the combustor casing fuel injector includes a fuel manifold adjacent to an outer surface of the combustor casing. In certain embodiments, the combustor casing fuel injector includes a fuel injector; wherein the fuel injector extends through the combustor casing from a position within the fuel manifold to a predetermined fuel injection location; and wherein the fuel injector includes a protruding injector inlet within the fuel manifold.
    Type: Application
    Filed: July 6, 2011
    Publication date: January 10, 2013
    Inventors: Keith Cletus Belsom, Donald Timothy Lemon
  • Conical swirler for fuel injectors and combustor domes and methods of manufacturing the same
    Patent number: 8348180
    Abstract: A method of manufacturing gas and/or fuel swirlers for fuel injectors and combustor domes and cone-shaped swirlers so manufactured are disclosed. The disclosed conical swirlers feature cut-through slots on a cone-shaped body. The contour and spacing of the slots are configured and arranged to accommodate a wide range of requirements for fluid flow areas and swirl strengths. Preferably, the cone-shaped swirlers can be manufactured by wire EDM processing. More preferably, multiple cone-shaped swirlers can be manufactured simultaneously by nesting swirler blanks in a stack and wire EDM processing the stack as a unit. The cone-shaped pinwheel swirler fits well into various fuel injector heads, enabling the injectors to reduce the frontal surface area and flat area for minimal potential of carbon formation.
    Type: Grant
    Filed: June 9, 2004
    Date of Patent: January 8, 2013
    Assignee: Delavan Inc
    Inventors: Chien-Pei Mao, John Short
  • Fuel nozzle liquid cartridge including a fuel insert
    Patent number: 8347631
    Abstract: In an embodiment, a system includes an end cover and a liquid cartridge. The liquid cartridge is configured to mount in a fuel nozzle of a turbine engine, wherein the liquid cartridge comprises a one piece flange configured to couple to the end cover, wherein the flange comprises a water inlet, an air inlet, and a fuel inlet.
    Type: Grant
    Filed: March 3, 2009
    Date of Patent: January 8, 2013
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Scott R Simmons, Gregory Allen Boardman, Xiomara Irizarry-Rosado
  • Air-blast fuel-injector with shield-cone upstream of fuel orifices
    Patent number: 8347630
    Abstract: An air-blast fuel nozzle assembly includes a housing having an inner surface defining an interior chamber around a central axis. The inner surface terminates in an exit aperture. An air swirler pneumatically communicates with the interior chamber and has vanes operative to impart a swirling motion to air passing across the vanes and into the interior chamber. A fuel injection assembly includes a nozzle portion extending along the central axis and having a plurality of outlets circumferentially-arranged around the central axis that are directed into the interior chamber toward the inner surface of the housing. A shield extends radially outwardly from the nozzle portion upstream of the plurality of outlets. The shield extends between a base at the nozzle section and a free tip end such that the shield extends partially across the interior chamber toward the inner surface.
    Type: Grant
    Filed: September 3, 2008
    Date of Patent: January 8, 2013
    Assignee: United Technologies Corp
    Inventors: Jeffery A. Lovett, Frederick C. Padget, John W. Mordosky, Shawn M. McMahon
  • GAS TURBINE COMBUSTION BURNER
    Publication number: 20130000306
    Abstract: In a gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel spraying hole that sprays fuel into a combustion region formed inside a combustion cylinder of a gas-turbine combustor and in which a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel spraying hole is formed in the interior thereof, the impedance of a fuel supply system that guides the fuel from the fuel source to the fuel spraying hole is set so that propagation of pressure fluctuations from the combustion region to the fuel supply system becomes an allowable level or less.
    Type: Application
    Filed: June 13, 2012
    Publication date: January 3, 2013
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Keisuke Matsuyama, Takanori Ito, Tei Yamato, Koji Maeta, Sosuke Nakamura
  • Fuel distributor
    Patent number: 8336313
    Abstract: A unitary distributor is disclosed, comprising at least one main flow passage located within a distributor ring body, the main flow passage having an arcuate portion oriented in a circumferential direction around a distributor axis. Exemplary embodiments of a unitary distributor having an annular ring located at the axially forward end of the distributor ring body are disclosed. A fuel distributor is disclosed, comprising a fuel conduit and a distributor wherein the fuel distributor has a unitary construction.
    Type: Grant
    Filed: July 30, 2008
    Date of Patent: December 25, 2012
    Assignee: General Electric Company
    Inventors: Marie Ann McMasters, Michael A. Benjamin, Alfred Mancini
  • Gas turbine premixer with internal cooling
    Patent number: 8333075
    Abstract: 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.
    Type: Grant
    Filed: April 16, 2009
    Date of Patent: December 18, 2012
    Assignee: General Electric Company
    Inventors: William David York, Thomas Edward Johnson, Benjamin Paul Lacy, Christian Xavier Stevenson
  • Gas turbine fuel injector assembly with overlapping frictionally engaged members for damping vibrations
    Patent number: 8327649
    Abstract: Fuel injector assemblies with frictionally damped fuel supply members, including fuel feed strips. More particularly, the invention provides friction dampers and/or assemblies that frictionally damp movement of fuel supply members in at least one direction. Some of the embodiments provide a friction damper that is easily serviceable, and can be installed after final assembly of a fuel injector. Aspects of the invention are applicable to other components of fuel injectors and gas turbine engines in addition to fuel supply members.
    Type: Grant
    Filed: March 22, 2011
    Date of Patent: December 11, 2012
    Assignee: Parker-Hannifin Corporation
    Inventors: Fady Bishara, Jeffrey Lehtinen
  • Multiple tube premixing device
    Patent number: 8327642
    Abstract: The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes.
    Type: Grant
    Filed: October 21, 2008
    Date of Patent: December 11, 2012
    Assignee: General Electric Company
    Inventors: Jong Ho Uhm, Balachandar Varatharajan, Willy Steve Ziminsky, Gilbert Otto Kraemer, Ertan Yilmaz, Benjamin Lacy, Christian Stevenson, David Felling
  • INTEGRATED FUEL NOZZLE AND IGNITION ASSEMBLY FOR GAS TURBINE ENGINES
    Publication number: 20120304651
    Abstract: There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage.
    Type: Application
    Filed: May 30, 2011
    Publication date: December 6, 2012
    Inventors: BHAWAN B. PATEL, Enzo Macchia, Oleg Morenko, George Guglielmin