Plural Distinct Injectors Patents (Class 60/746)
  • Publication number: 20130174560
    Abstract: A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct.
    Type: Application
    Filed: December 18, 2012
    Publication date: July 11, 2013
    Inventors: DAVID J. WIEBE, TIMOTHY A. FOX
  • Publication number: 20130174569
    Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and a plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the distribution manifold provides fluid communication through the distribution manifold to the plurality of fuel injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber and diverting a portion of the working fluid through a distribution manifold that circumferentially surrounds a plurality of fuel injectors circumferentially arranged around the combustion chamber.
    Type: Application
    Filed: January 6, 2012
    Publication date: July 11, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Lucas John Stoia, Patrick Benedict Melton
  • Publication number: 20130174561
    Abstract: A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface.
    Type: Application
    Filed: January 9, 2012
    Publication date: July 11, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Lucas John Stoia, Patrick Benedict Melton
  • Patent number: 8479521
    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: January 24, 2011
    Date of Patent: July 9, 2013
    Assignee: United Technologies Corporation
    Inventor: James B. Hoke
  • Patent number: 8474265
    Abstract: A fuel nozzle for a turbine engine includes a primary fuel passageway for supplying fuel to a plurality of radially extending fuel injectors arranged around the exterior of the fuel nozzle. A secondary fuel passageway couples an upstream end of the primary fuel passageway to a downstream end of the primary fuel passageway. The secondary fuel passageway acts as a resonator tube to help reduce oscillations in the fuel flowing through the primary fuel passageway.
    Type: Grant
    Filed: July 29, 2009
    Date of Patent: July 2, 2013
    Assignee: General Electric Company
    Inventors: Praveen Babulal Jain, Narayan Subramanian
  • Patent number: 8468832
    Abstract: An object of this invention is to suppress adhesion of a flame to periphery of air hole outlets arranged on an air hole plate. A combustor includes a fuel nozzle for jetting out a fuel into a combustion chamber formed at a downstream side; an air hole plate of a flat-plate shape disposed between the fuel nozzle and the chamber, the air hole plate facing an upstream side of the chamber; and a plurality of air holes provided in the air hole plate, in a circumferential direction relative to a central axis of the air hole plate, such that a fuel flow and an air flow formed at an outer circumferential side of the fuel flow are blown out into the chamber from the respective air holes; wherein a clearance defined between any two circumferentially adjacent air hole inlets provided on a face of the air hole plate that is nearer to the fuel nozzle is wider than a clearance defined between any two circumferentially adjacent air hole outlets formed on a face of the air hole plate that is nearer to the chamber.
    Type: Grant
    Filed: August 18, 2009
    Date of Patent: June 25, 2013
    Assignee: Hitachi, Ltd.
    Inventors: Satoshi Dodo, Keisuke Miura, Kazuhito Koyama
  • Patent number: 8464539
    Abstract: A nozzle assembly (10) comprising a first inlet tube (14), a second inlet tube (15), and a nozzle (16). The nozzle (16) is formed from a stack of plates (20-38) which are joined together in face-to-face contact. The plates (20-38) collectively have openings which define a nozzle outlet, a first inlet, a second inlet, a first circuit from the first inlet to the nozzle outlet, a second circuit from the second inlet to the nozzle outlet, and a fluid-outlet chamber through which both the first circuit and the second circuit pass. The nozzle assembly (10) can be used as a fuel injector for a gas turbine engine, with jet fuel being supplied to the first circuit during start-up and low power conditions and jet fuel being supplied to both the first circuit and the second circuit during high power conditions.
    Type: Grant
    Filed: February 4, 2009
    Date of Patent: June 18, 2013
    Assignee: Parker-Hannifin Corporation
    Inventors: Robert R. Pelletier, James R. Pavlik
  • Patent number: 8464538
    Abstract: A trapped vortex combustor includes a trapped vortex cavity having a first surface and a second surface. A plurality of fluidic mixers are disposed circumferentially along the first surface and the second surface of the trapped vortex cavity. At least one fluidic mixer includes a first open end receiving a first fluid stream, a coanda profile in the proximity of the first open end, a fuel plenum to discharge a fuel stream over the coanda profile, and a second open end for receiving the mixture of the first fluid stream and the fuel stream and discharging the mixture of the first fluid stream and the fuel stream in the trapped vortex cavity. The coanda profile is configured to enable attachment of the fuel stream to the coanda profile to form a boundary layer of the fuel stream and, to entrain the incoming first fluid stream to the boundary layer of the fuel stream to form a mixture of the first fluid stream and the fuel stream.
    Type: Grant
    Filed: December 17, 2010
    Date of Patent: June 18, 2013
    Assignee: General Electric Company
    Inventors: Andrei Tristan Evulet, Gustavo Adolfo Ledezma, Corey Bourassa
  • Publication number: 20130145741
    Abstract: A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. A first and a second combustion stages are defined between the liners, each said combustion stage having a plurality of fuel injection bores distributed in a liner wall defining the respective stage. Valves at the fuel injection bores of one of the combustion stages, the valves each defining an air passage from an exterior to an interior of the combustion stage, the valves each having an actuatable member for adjusting a size of a respective air passage for air staging the combustor.
    Type: Application
    Filed: December 7, 2011
    Publication date: June 13, 2013
    Inventors: Eduardo HAWIE, Nigel Davenport
  • 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
  • Patent number: 8438853
    Abstract: A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate.
    Type: Grant
    Filed: October 8, 2008
    Date of Patent: May 14, 2013
    Assignee: Alstom Technology Ltd.
    Inventors: Andrew Green, Peter Stuttaford, Yan Chen, Hany Rizkalla
  • 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
  • Publication number: 20130091824
    Abstract: The invention provides a gas-turbine fuel nozzle (1) that includes a plurality of fuel supply channels (3a) to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels (3b) to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes (7a, 7b) that are provided at downstream ends of the fuel supply channels (3a) or the fuel/scavenging-fluid supply channels (3b) and that inject the fuel guided from the fuel supply channels (3a) or the fuel/scavenging-fluid supply channels (3b); a scavenging-fluid supply channel (21) that is connected to the fuel/scavenging-fluid supply channels (3b) to guide the scavenging fluid; and scavenging-fluid cooling means (23) for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel.
    Type: Application
    Filed: October 27, 2011
    Publication date: April 18, 2013
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Masayuki Murakami, Kazuya Higashi, Yukimasa Nakamoto, Satoko Fujii, Takeyuki Shimizu, Keigo Matsumoto
  • Publication number: 20130086882
    Abstract: A power plant is provided and includes a gas turbine engine having a combustor in which compressed gas and fuel are mixed and combusted, first and second supply lines respectively coupled to the combustor and respectively configured to supply the compressed gas and the fuel to the combustor and an exhaust gas recirculation (EGR) system to re-circulate exhaust gas produced by the gas turbine engine toward the combustor. The EGR system is coupled to the first and second supply lines and configured to combine first and second portions of the re-circulated exhaust gas with the compressed gas and the fuel at the first and second supply lines, respectively.
    Type: Application
    Filed: October 7, 2011
    Publication date: April 11, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Ashok Kumar Anand, Thirumala Reddy Nagarjuna Reddy, Jason Brian Shaffer, William David York
  • Publication number: 20130086913
    Abstract: A turbomachine combustor includes a combustor cap having a cap surface and a wall that extends about the cap surface to define a cap volume, and a plurality of nozzle members that extend from the cap surface. The plurality of nozzle members include a center nozzle member and one ore more outer nozzle members. A combustor dynamics mitigation system is arranged in the combustor cap and includes plurality of divider members that extend from the wall toward the center nozzle member. The plurality of divider members define a plurality of parallel resonator volumes. The combustor dynamics mitigation system also includes a plurality of tubes that extend into corresponding ones of the plurality of parallel resonator volumes.
    Type: Application
    Filed: October 7, 2011
    Publication date: April 11, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Mahesh Bathina, Madanmohan Manoharan
  • Publication number: 20130086912
    Abstract: A system includes a multi-tube fuel nozzle including a fuel nozzle head that includes an outer wall surrounding a chamber. The outer wall includes a downstream wall portion configured to face a combustion region. The multi-tube fuel nozzle also includes multiple tubes extending through the chamber to the downstream wall portion. Each tube of the multiple tubes includes an upstream portion, a downstream portion, and at least one fuel inlet disposed at the upstream portion, and is configured to receive air and mix the air with fuel from the at least one fuel inlet. The multi-tube fuel nozzle includes a fuel conduit extending through the chamber crosswise to and around the multiple tubes. The fuel conduit includes multiple impingement cooling orifices. A fuel flow path extends through the fuel conduit, through the impingement cooling orifices, through the chamber, and into the at least one fuel inlet of each tube.
    Type: Application
    Filed: October 6, 2011
    Publication date: April 11, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Jonathan Dwight Berry
  • 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
  • Publication number: 20130074505
    Abstract: A system includes a gas turbine combustor. The gas turbine combustor includes a combustion liner disposed about a combustion region and a sleeve disposed about the combustion liner. The combustion liner and the sleeve define an airflow passage circumferentially about the liner. The gas turbine combustor also includes multiple axial injectors configured to direct an airflow into the airflow passage in an axial direction facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor. The multiple axial injectors are asymmetrically configured to provide an uniform injection of the airflow circumferentially about an axis of the gas turbine combustor.
    Type: Application
    Filed: September 22, 2011
    Publication date: March 28, 2013
    Applicant: General Electric Company
    Inventors: David Kaylor Toronto, Carolyn Ashley Antoniono, Andrew Grady Godfrey
  • Publication number: 20130074506
    Abstract: A turbine burner is provided. The turbine burner has a secondary feed unit and a primary feed unit. The primary feed unit has a primary mixing tube and a fuel nozzle that are arranged concentrically around the secondary feed unit. The primary mixing tube and the fuel nozzle have a fluid flow connection. The fuel nozzle has an annular wall that is radially spaced in the axial direction from the secondary feed unit such that a gap height is fainted by the annular wall and the secondary feed unit. The annular wall has an inside wall directed toward the secondary feed unit and having blades with a leading edge on the upstream side. The fuel nozzle has an inlet and the blades have an axial distance from the inlet. The ratio of the distance to the gap height is greater than 1 and less than the gap height.
    Type: Application
    Filed: March 29, 2011
    Publication date: March 28, 2013
    Inventors: Boris Ferdinand Kock, Berthold Köstlin, Bernd Prade
  • Patent number: 8402763
    Abstract: A combustor for a gas turbine includes a plurality of nozzles provided in an array; a baffle plate configured to provide a desired air flow distribution to the array of nozzles; and a casing comprising a plurality of holes in an outer surface. The casing extends from a headend of the combustor to the baffle plate. A method of distributing an air flow in a combustor of a gas turbine includes providing an air flow to the outer surface of the casing; directing the air flow around the baffle plate; and distributing the air flow through the baffle plate to the array of nozzles.
    Type: Grant
    Filed: October 26, 2009
    Date of Patent: March 26, 2013
    Assignee: General Electric Company
    Inventors: Jason Mulherin, John Charles Intile
  • Publication number: 20130067921
    Abstract: A fuel injector is provided and includes a member defining a flowpath through which a first fluid flows, the flowpath having a cross-section with transverse elongate and short axes, a head defining a plenum storing a supply of a second fluid and a system fluidly coupled to the flowpath and the plenum to inject the second fluid from the plenum and into the flowpath at first and second locations along the elongate axis. The injected second fluid is formed into jets at the first and second locations, the first fluid entrains the jets such that the injected second fluid flows through the flowpath and mixes with the first fluid, and the short axis has a sufficient dimension such that the jets remain spaced from a sidewall of the member.
    Type: Application
    Filed: September 15, 2011
    Publication date: March 21, 2013
    Applicant: General Electric Company
    Inventors: Mark Allan Hadley, Jun Cai, Lucas John Stoia, Geoffrey David Myers, Jayaprakash Natarajan
  • 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
  • Publication number: 20130061598
    Abstract: A system for conditioning a working fluid in a combustor includes a primary combustion chamber, a liner circumferentially surrounding the primary combustion chamber, and a primary nozzle in fluid communication with the primary combustion chamber. A secondary combustion chamber located outside of the primary combustion chamber includes a shroud that defines a fluid passage, a secondary nozzle, and means for igniting fuel in the secondary combustion chamber. A method for conditioning a working fluid in a combustor includes flowing the working fluid through a primary combustion chamber and flowing at least a portion of the working fluid through a secondary combustion chamber located outside of the primary combustion chamber. The method further includes flowing a fuel through the secondary combustion chamber, combusting the fuel, and flowing the combustion gases from the secondary combustion chamber into the primary combustion chamber.
    Type: Application
    Filed: September 14, 2011
    Publication date: March 14, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Stanley Kevin Widener
  • Patent number: 8393891
    Abstract: 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.
    Type: Grant
    Filed: September 18, 2006
    Date of Patent: March 12, 2013
    Assignee: General Electric Company
    Inventors: Gregory Allen Boardman, Thomas Edward Johnson
  • 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
  • Publication number: 20130055720
    Abstract: A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures define a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.
    Type: Application
    Filed: September 7, 2011
    Publication date: March 7, 2013
    Inventors: TIMOTHY A. FOX, Reinhard Schilp
  • Patent number: 8387392
    Abstract: Disclosed herein is a fuel injection system, including: a fuel injection module including a primary fuel injector and one or more secondary fuel injectors disposed around the primary fuel injector; an air supply module for supplying air to the fuel injection module inwardly and outwardly; and a fuel supply module for supplying fuel to the fuel injection module, wherein the fuel injection module serves to generate multistage flames in a burner by forming a rich fuel flame region using the primary fuel injector and forming a lean fuel flame region behind the rich fuel flame region using the secondary fuel injectors through a burning process of gasifying secondary fuel.
    Type: Grant
    Filed: December 18, 2008
    Date of Patent: March 5, 2013
    Assignee: Korea Institute of Industrial Technology
    Inventors: Se Won Kim, Myung Chul Shin, Chang Yeop Lee
  • Patent number: 8387394
    Abstract: A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.
    Type: Grant
    Filed: July 2, 2008
    Date of Patent: March 5, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventors: Matthias Hase, Michael Huth, Robert Angel, Drew Ehlert, James Marshall, Yevgeniy Shteyman
  • 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
  • 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
  • Publication number: 20130042622
    Abstract: A flow balancing valve for a multistage combustor includes a first pressure feedback line, a first burn line, and a first metering port fluidly connected to the first fuel injector. The flow balancing valve further includes a second pressure feedback line, a second burn line, and a second metering port fluidly connected to the second fuel injector. A metering land is located between and defines sizes of the first metering port and the second metering port. An increase in pressure differential between the first pressure feedback line and the second pressure feedback line causes a compensatory movement in the metering land to balance fuel flow for the first fuel injector and the second fuel injector.
    Type: Application
    Filed: August 17, 2011
    Publication date: February 21, 2013
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Thaddeus J. Zebrowski
  • Publication number: 20130036741
    Abstract: A multipoint combustion system for a gas turbine engine includes a housing defining a pressure vessel. A master injector is mounted to the housing for injecting fuel along a central axis. A plurality of slave injectors are each disposed outward of the master injector for injecting fuel and air in an ignition plume radially outward of fuel injected through the master injector. The master injector and slave injectors are configured and adapted so the injection plume of the master injector intersects with the ignition plumes of the slave injectors. A primary manifold is included within the pressure vessel for distributing fuel to the slave injectors. An auxiliary manifold is in fluid communication with the auxiliary nozzles of the slave injectors for issuing an auxiliary flow of fuel from the auxiliary nozzles that is separate from the fuel flow of the primary manifold.
    Type: Application
    Filed: October 9, 2012
    Publication date: February 14, 2013
    Applicant: Delavan Inc
    Inventor: Lev Alexander Prociw
  • 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
  • Publication number: 20130014512
    Abstract: A vane assembly has an outer support ring, an inner support ring, an outer liner ring, an inner liner ring, and a circumferential array of vanes. Each vane has a shell extending from an inboard end to an outboard end and at least partially through an associated aperture in the inner liner ring and an associated aperture in the outer liner ring. There is at least one of: an outer compliant member compliantly radially positioning the vane; and an inner compliant member compliantly radially positioning the vane.
    Type: Application
    Filed: July 13, 2011
    Publication date: January 17, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: David C. Jarmon, Peter G. Smith
  • Publication number: 20130000311
    Abstract: A fuel injection array for a gas turbine engine includes a plurality of bluff body injectors and a plurality of swirler injectors. A control operates the plurality of bluff body injectors and swirler injectors such that bluff body injectors are utilized without all of the swirler injectors at least at low power operation. The swirler injectors are utilized at higher power operation.
    Type: Application
    Filed: June 28, 2011
    Publication date: January 3, 2013
    Inventor: Timothy S. Snyder
  • Publication number: 20120324863
    Abstract: A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body.
    Type: Application
    Filed: May 7, 2012
    Publication date: December 27, 2012
    Applicant: ALSTOM Technology Ltd
    Inventors: Anton WINKLER, Urs BENZ, Andre THEUER, Diane LAUFFER, Madhavan POYYAPAKKAM
  • 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
  • Patent number: 8340886
    Abstract: A system includes a turbine fuel controller. The turbine fuel controller includes a purge control logic configured to control a purge sequence of mixing a purge gas with a first fuel during a first fuel shutdown, wherein the purge sequence is configured to open a purge valve for the purge gas before fully closing a fuel valve for the first fuel.
    Type: Grant
    Filed: March 7, 2011
    Date of Patent: December 25, 2012
    Assignee: General Electric Company
    Inventors: Vijay Raghavendran Nenmeni, Michael John Rozdolski, Rahul Jaikaran Chillar
  • 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
  • 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
  • Publication number: 20120304654
    Abstract: A combustor for a turbine is provided. The combustor includes a plurality of fuel nozzles and a combustion zone is aligned with a combustion process associated with each of the fuel nozzles. A combustion liner includes a plurality of turbulator groups, and each of the turbulator groups has or more individual turbulators. Each of the turbulator groups is aligned with a hot streak caused by the combustion zone associated with the fuel nozzle. Each of the turbulator groups are circumferentially spaced from a neighboring turbulator group.
    Type: Application
    Filed: June 6, 2011
    Publication date: December 6, 2012
    Inventors: Patrick Benedict Melton, David William Cihlar, David Kaylor Toronto
  • Patent number: 8316644
    Abstract: The invention relates to a burner, in particular a gas turbine burner, comprises: at least one swirler, the swirler having at least one air inlet opening, at least one air outlet opening positioned downstream to the air inlet opening and at least one swirler air passage extending from the at least one air inlet opening to the at least one air outlet opening which is delimited by swirler air passage walls, the air passage walls comprising downstream wall sections adjoining the at least one air outlet opening; and a fuel injection system which comprises fuel injection openings arranged in at least one swirler air passage wall so as to inject fuel into the swirler air passage; in which at least the downstream section of one air passage wall is corrugated.
    Type: Grant
    Filed: February 27, 2007
    Date of Patent: November 27, 2012
    Assignee: Siemens Aktiengesellschaft
    Inventor: Nigel Wilbraham
  • Publication number: 20120291442
    Abstract: A rotationally symmetrical wall for an aircraft turbomachine combustion chamber, including primary holes, dilution holes positioned downstream from the primary holes, and a plug installation aperture upstream from the primary holes, wherein each first primary hole, considered as one moves away circumferentially from the median axial plane (D) in either direction is positioned at a circumferential position between the circumferential positions of the first dilution hole and of the second dilution hole considered as one moves away circumferentially from the median axial plane (D), wherein the other primary holes are distributed equidistantly, at a predefined interval P, and the distance between the two primary holes is greater than the interval P separating two of the other adjacent primary holes.
    Type: Application
    Filed: May 18, 2012
    Publication date: November 22, 2012
    Applicant: SNECMA
    Inventors: Patrice André Commaret, Jacques Marcel Arthur Bunel, Didier Hippolyte Hernandez
  • Publication number: 20120279224
    Abstract: A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
    Type: Application
    Filed: May 3, 2011
    Publication date: November 8, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Donald Mark Bailey, Jonathan Dwight Berry, Luis Manuel Flamand, Kwanwoo Kim, Patrick Benedict Melton, Robert Joseph Rohrssen, John Drake Vanselow
  • Patent number: 8297057
    Abstract: A fuel injector head for a gas turbine engine the head having a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric splitter separates the pilot injector from the main injector and has a toroid chamber which is supplied with air in use to generate a toroidal flow which delays mixing of the pilot and main air flows.
    Type: Grant
    Filed: December 5, 2008
    Date of Patent: October 30, 2012
    Assignee: Rolls-Royce, PLC
    Inventor: Ian J. Toon
  • Publication number: 20120266602
    Abstract: The present application and the resultant patent provide a combustor for a turbine engine. The combustor may include a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly. The swirler assembly may include a number of stages with a number of fueled structures and a number of unfueled structures.
    Type: Application
    Filed: April 22, 2011
    Publication date: October 25, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Joel Meier Haynes
  • Publication number: 20120260666
    Abstract: A multi-fuel combustion system is provided. The system includes a combustor basket adapted to combust at least two type of fuels. The combustor basket includes a circumferential wall with a plurality of openings. The combustion system further includes a first conduit adapted to provide a first type of fuel directly to the combustor basket and a second conduit adapted to provide a second type of fuel directly to the combustor basket. The combustion system also may include a third conduit adapted to inject at least one of the first type of fuel and the second type of fuel through the openings into the combustor basket.
    Type: Application
    Filed: October 20, 2010
    Publication date: October 18, 2012
    Inventors: Vinayak V. Barve, Timothy A. Fox, Jianfan Wu, Ulrich Wörz, Jaap Van Kampen
  • Patent number: 8281595
    Abstract: A fuel nozzle assembly for a combustor of a gas turbine including: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front proximate to a combustion section of the combustor; an outer casing around the inner tube, wherein an air passage is defined between the outer casing and the inner tube; a gas conduit arranged in the air passage and having an outlet proximate to the front of the nozzle body, wherein fuel starts flowing through the expandable conduit only after a flashback condition occurs in the combustor, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein the gas conduit has an inlet open to the premix fuel passage.
    Type: Grant
    Filed: May 28, 2008
    Date of Patent: October 9, 2012
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Stanley Kevin Widener, John Wilber
  • Patent number: 8276388
    Abstract: An annular expansion ring centered on a main axis and suitable for being mounted on a fuel injector coaxial with the ring is disclosed. The ring presents holes that are distributed around the main axis and open out into its upstream face to enable air to pass towards the zone that is downstream from the ring. The ring includes a conical annular groove that converges downstream, that is open downstream, and that has the holes opening out into the upstream portion thereof. The axis of each of the holes makes an angle relative to the main axis that is strictly greater than the angle between the generator line of the cone defining the annular groove and the main axis, such that the air exiting from the holes impacts against the inner wall of the annular groove, i.e. its wall that is closer to the main axis.
    Type: Grant
    Filed: July 1, 2008
    Date of Patent: October 2, 2012
    Assignee: Snecma
    Inventors: Alain Cayre, Christophe Pieussergues, Jackie Raymond Julien Prouteau, Denis Jean Maurice Sandelis
  • Publication number: 20120240592
    Abstract: The present application and the resultant patent provide a fuel nozzle for mixing a flow of air and a flow of fuel within a combustor. The fuel nozzle may have one or more air passages for the flow of air, one or more fuel pegs for the flow of fuel, and a liner in communication with the air passages and surrounding the fuel pegs. The liner may include a number of ribs thereon so as to promote mixing of the flow of air and the flow of fuel therein.
    Type: Application
    Filed: March 23, 2011
    Publication date: September 27, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Mayur Abhay Keny, Ronald Chila, Vaibhav Nadkarni