Plural Distinct Injectors Patents (Class 60/746)
  • Patent number: 10215412
    Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle is configured to produce a diffusion flame. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.
    Type: Grant
    Filed: October 30, 2013
    Date of Patent: February 26, 2019
    Assignees: General Electric Company, ExxonMobil Upstream Research Company
    Inventors: Richard A. Huntington, Sulabh K. Dhanuka, Ilya Aleksandrovich Slobodyanskiy
  • Patent number: 10082076
    Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: September 25, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi
  • Patent number: 10072846
    Abstract: A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.
    Type: Grant
    Filed: July 6, 2015
    Date of Patent: September 11, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sarah Marie Monahan, Narendra Digamber Joshi, Venkat Eswarlu Tangirala, Matthieu Marc Masquelet
  • Patent number: 10001281
    Abstract: A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis and having an exterior surface, and having a ring of forward openings passing through the exterior surface, and a ring of aft openings passing through the exterior surface, the aft openings positioned axially aft of the forward openings; an annular main injection ring disposed inside the outer body and including: a forward main fuel gallery extending in a circumferential direction; an aft main fuel gallery extending in a circumferential direction; a ring of forward main fuel orifices communicating with the forward main fuel gallery and each aligned with one of the forward openings; a ring of aft main fuel orifices, communicating with the aft main fuel gallery and each aligned with one of the aft openings; and a pilot fuel injector disposed along the centerline axis.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: June 19, 2018
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Duane Douglas Thomsen
  • Patent number: 9964309
    Abstract: A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.
    Type: Grant
    Filed: December 22, 2014
    Date of Patent: May 8, 2018
    Assignee: General Electric Company
    Inventors: Donald Michael Corsmeier, Mark Eugene Noe, Michael Todd Radwanski, Oliver Roghe, Jessica Licardi Subit, Ming Xie
  • Patent number: 9958162
    Abstract: A combustor assembly includes a first wall, a second wall, a bulkhead and a plurality of fuel injectors. The bulkhead forms a combustion chamber with the first and the second walls. The fuel injectors are configured with the first wall in a unique and/or a fluctuating pattern.
    Type: Grant
    Filed: July 18, 2014
    Date of Patent: May 1, 2018
    Assignee: United Technologies Corporation
    Inventors: Zhongtao Dai, Jeffrey M. Cohen, Kristin Kopp-Vaughan, James B. Hoke
  • Patent number: 9803555
    Abstract: A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor.
    Type: Grant
    Filed: April 23, 2014
    Date of Patent: October 31, 2017
    Assignee: General Electric Company
    Inventors: Robert Joseph Rohrssen, David William Cihlar, Patrick Benedict Melton, Lucas John Stoia
  • Patent number: 9803552
    Abstract: A fuel injection system for use in a combustor of a turbine assembly includes a substantially annular fuel injection housing at least partially defining an annular cavity. The fuel injection system also includes a fuel manifold and an air manifold. The fuel manifold includes a plurality of fuel injection ports extending through the fuel injection housing. The air manifold includes a first plurality of air injection ports and a second plurality of air injection ports that each extends through the fuel injection housing.
    Type: Grant
    Filed: October 30, 2015
    Date of Patent: October 31, 2017
    Assignee: General Electric Company
    Inventors: Yuxin Zhang, Obulesu Chatakonda, Soumya Gudiyella, Narendra Digamber Joshi, Venkat Eswarlu Tangirala, Matthieu Marc Masquelet, Shashank Yellapantula
  • Patent number: 9765972
    Abstract: A fuel injector for a gas turbine engine includes a monolithic nozzle body that defines within its interior one or more fuel circuits. Each fuel circuit includes an inlet, an outlet orifice, a main passage fluidly coupling the inlet with the outlet orifice, and a branch passage connected to the main passage. The branch passage connects to the main passage downstream of the inlet and upstream of the outlet orifice to form an effective metering flow area that is smaller than the flow area of the outlet orifice.
    Type: Grant
    Filed: January 30, 2015
    Date of Patent: September 19, 2017
    Assignee: Delavan Inc.
    Inventor: Gregory Zink
  • Patent number: 9752781
    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: Grant
    Filed: September 26, 2013
    Date of Patent: September 5, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Peter John Stuttaford, Stephen Jorgensen, Timothy Hui, Yan Chen, Hany Rizkalla, Khalid Oumejjoud
  • Patent number: 9714768
    Abstract: A gas turbine engine that includes: a combustor coupled to a turbine and a downstream injection system that includes two injection stages, a first stage and a second stage, positioned within an interior flowpath, wherein the first stage comprises an axial position that is aft of the primary air and fuel injection system and the second stage comprising an axial position that is aft of the first stage. Each of the first stage and the second stage include a plurality of circumferentially spaced injectors, each injector of which is configured to inject air and fuel into a flow through the interior flowpath. The first stage and the second stage have a configuration that limits a fuel injected at the second stage to less than 50% of a fuel injected at the first stage.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: July 25, 2017
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Kaitlin Marie Graham
  • Patent number: 9551489
    Abstract: An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.
    Type: Grant
    Filed: September 25, 2012
    Date of Patent: January 24, 2017
    Assignee: SNECMA
    Inventors: Matthieu Francois Rullaud, Michel Pierre Cazalens
  • Patent number: 9435541
    Abstract: A gas turbine that includes: a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a primary air and fuel injection system that defines a forward end, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end; and a downstream injection system that includes two injection stages, a first stage and a second stage, that are axially spaced along the longitudinal axis of the interior flowpath. The first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: September 6, 2016
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Kaitlin Marie Graham
  • Patent number: 9310080
    Abstract: An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.
    Type: Grant
    Filed: August 11, 2014
    Date of Patent: April 12, 2016
    Assignee: ROLLS-ROYCE PLC
    Inventor: Ian James Toon
  • Patent number: 9157370
    Abstract: A burner assembly is provided. The burner assembly includes a support housing with a supply manifold, the supply manifold includes a fuel passage system, and fuel nozzles extending from the supply manifold and being supplied with fuel through the fuel passage system of the supply manifold. The supply manifold is sandwiched using at least two subparts.
    Type: Grant
    Filed: February 23, 2010
    Date of Patent: October 13, 2015
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Andreas Böttcher, Timothy A. Fox, Thomas Grieb, Birgit Grüger, Tobias Krieger, Stephen A. Ramier, Christin Schlensog, Holger Streb
  • Patent number: 9080770
    Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.
    Type: Grant
    Filed: June 6, 2011
    Date of Patent: July 14, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Veeraraghave Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini
  • Publication number: 20150128601
    Abstract: A gas turbine combustor having a burner including a plurality of fuel nozzles for injecting fuel, air hole plates positioned on a downstream side of the fuel nozzles and a plurality of air holes arranged in pairs with each of the fuel nozzles, and a combustion chamber for mixing fuel injected from the fuel nozzles and air injected from the air holes and injecting and burning the mixed fuel. Each of the fuel nozzles configuring the burners is provided with a projection in which a part of an outer edge of a section of the fuel nozzle is protruded outward; and the projection is arranged so as to be directed toward a center of the gas turbine combustor. The projection of the fuel nozzle is positioned on a downstream side of a flow of combustion air flowing around each of the fuel nozzles.
    Type: Application
    Filed: November 12, 2014
    Publication date: May 14, 2015
    Inventors: Yoshinori MATSUBARA, Keisuke MIURA
  • Patent number: 9027349
    Abstract: A combustor of the prior art that defines the outlet position and direction of an air hole and suppresses adhesion of flame to an air hole outlet can reduce a discharge amount of NOx by increasing a distance over which fuel and air are mixed with each other. However, such a combustor is not sufficiently discussed for measures to suppress the occurrence of combustion oscillation resulting from the variation of a flame surface. A combustor 2 according to the present invention includes a combustion chamber 5 to which fuel and air are supplied; air holes 32 adapted to supply air to the combustion chamber 5; fuel nozzles 25 adapted to supply gaseous fuel to the air holes 32; and orifices 24 adapted to allow the gaseous fuel supplied to the air holes 32 to cause a pressure drop.
    Type: Grant
    Filed: January 25, 2012
    Date of Patent: May 12, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Keisuke Miura, Tomomi Koganezawa, Satoshi Dodo, Takeo Saito
  • Patent number: 9016066
    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: Grant
    Filed: December 18, 2012
    Date of Patent: April 28, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: David J. Wiebe, Timothy A. Fox
  • Patent number: 9016601
    Abstract: A swirler including a fuel distributor is provided. Each fuel distributor includes a distribution element defining a cavity, an inlet opening arranged in the distribution element, at least one outlet opening arranged in the distribution element, and at least one third opening arranged in the distribution element, the cross-section of the at least one third opening being larger than the cross-section of the at least one outlet opening.
    Type: Grant
    Filed: May 9, 2008
    Date of Patent: April 28, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Paul Headland, Richard Noden
  • Patent number: 9010120
    Abstract: A transfer tube for use in a late lean injection system of a combustor, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the outer radial wall including a late lean nozzle, the transfer tube including flow directing structure that defines a fluid passageway. At a first end, the flow directing structure may include an inlet and attachment means that attach the transfer tube to the late lean nozzle. The flow directing structure may have a configuration such that the fluid passageway spans the flow annulus and positions the outlet at a desirable injection point in the inner radial wall.
    Type: Grant
    Filed: August 5, 2011
    Date of Patent: April 21, 2015
    Assignee: General Electric Company
    Inventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia
  • Patent number: 9010119
    Abstract: A premixing nozzle of a combustor is provided and includes a gas premixer module, a centerbody, which is breech-loadable into the gas premixer module and a deformable, compliant interface between the gas premixer module and the centerbody.
    Type: Grant
    Filed: November 3, 2010
    Date of Patent: April 21, 2015
    Assignee: General Electric Company
    Inventor: Geoffrey David Myers
  • Patent number: 9003802
    Abstract: A fuel injector device for an annular combustion chamber of a turbine engine, including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular ring mounted in an annular chamber, together with a thermal insulation mechanism insulating the front face and including an annular cavity formed around the injection orifices between the front face of the annular ring and a front wall of the annular chamber and configured to be filled in operation with air or with coked fuel.
    Type: Grant
    Filed: October 6, 2010
    Date of Patent: April 14, 2015
    Assignee: SNECMA
    Inventors: Didier Hippolyte Hernandez, Emilie Lachaud, Thomas Olivier Marie Noel
  • Patent number: 9003804
    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: Grant
    Filed: October 9, 2012
    Date of Patent: April 14, 2015
    Assignee: Delavan Inc
    Inventor: Lev Alexander Prociw
  • Publication number: 20150089954
    Abstract: Burners having a fuel plenum in a base are disclosed. One disclosed example apparatus includes a base of a burner, the base comprising a fuel plenum and coupled to fuel nozzles, where at least one of the fuel nozzles is in fluid communication with the fuel plenum. The disclosed example apparatus also includes a burner head of the burner comprising nozzle passages in fluid communication with an airflow path, where the burner head defines a pilot combustion space that opens towards a flame tube of the burner, and is in fluid communication with the airflow path, and where each nozzle passage is to receive a fuel nozzle to provide fuel to entrain with air from the airflow path.
    Type: Application
    Filed: December 8, 2014
    Publication date: April 2, 2015
    Inventors: Axel Widenhorn, Roland Stoll, Dominik Lebküchner, Thilo Kissel
  • Publication number: 20150082801
    Abstract: It is proposed a gas turbine and a method to operate the gas turbine. A fluid is supplied to the gas turbine by means of fluid paths. A first fluid path is divided into a second and third fluid path. A first control valve controls a fluid mass flow in the first fluid path. A second control valve controls a ratio of fluid mass flows in the second and third fluid paths.
    Type: Application
    Filed: September 22, 2014
    Publication date: March 26, 2015
    Inventors: Susanne Renate SCHELL, Christoph GAUPP, Axel HAERMS, Richard CROMPTON, Eric Andre MUELLER
  • Publication number: 20150082796
    Abstract: A burner of a gas turbine extending along an axis is provided having in axial order: a swirler section, mixing section, outlet section, and main combustion zone. The swirler section has swirler vanes to swirl a stream of fuel and oxygen containing gas entering therein in a circumferential direction. The mixing section conducts the premix of fuel and oxygen containing gas to the outlet section. The outlet section discharges the premix into the combustion zone expanding the flow of premix from a smaller axial cross section of the mixing section to a larger cross section of the combustion zone which streamlines the flow to diverge radially. A surface of the outlet section facing the flow of the premix is provided with first fuel nozzles injecting fuel into the premix into a radial inwardly inclined direction before the flow of the premix enters the outlet section into the combustion zone.
    Type: Application
    Filed: April 8, 2013
    Publication date: March 26, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventors: Mats Andersson, Alessio Bonaldo
  • Publication number: 20150082770
    Abstract: A dual-fuel burning gas turbine combustor having a diffusive combustion burner to burn a liquid fuel and a gaseous fuel placed at the axis of the gas turbine combustor and a plurality of pre-mixing combustion burners to burn a liquid fuel and a gaseous fuel placed on an outer circumferential side of the diffusive combustion burner, each pre-mixing combustion burner having a liquid fuel nozzle, a plurality of gaseous fuel spray holes, a plurality of air holes, and a pre-mixing chamber to mix gaseous fuel and air, wherein each pre-mixing combustion burner has a double pipe sleeve at a connected portion between end cover and the pre-mixing combustion burner, and the double pipe sleeve has an inner sleeve having a gaseous fuel flow path, an outer sleeve positioned on an outer circumferential side of the inner sleeve, and a circular spacing formed between the inner sleeve and the outer sleeve.
    Type: Application
    Filed: August 18, 2014
    Publication date: March 26, 2015
    Inventors: Shota IGARASHI, Hirokazu TAKAHASHI
  • Publication number: 20150082797
    Abstract: A fuel injection device for supplying a fuel to a compressed air includes: a pilot fuel injector; a main fuel injector located at an outer periphery of the pilot fuel injector; and an air injection unit located between an outlet end portion of the pilot fuel injector and the main fuel injector. The air injection unit includes: a partition wall plate separating the air injection unit from a combustion chamber; a flame stabilization plate provided at a downstream side of the partition wall plate; a first opening at a downstream side between the flame stabilization plate and the outlet end portion of the pilot fuel injector; and a second opening provided in the partition wall plate and through which the compressed air is supplied. The flame stabilization plate includes an inclined portion inclined in a radially outward and downstream direction with respect to an axis.
    Type: Application
    Filed: December 2, 2014
    Publication date: March 26, 2015
    Applicants: KAWASAKI JUKOGYO KABUSHIKI KAISHA, JAPAN AEROSPACE EXPLORATION AGENCY
    Inventors: Ryusuke MATSUYAMA, Masayoshi KOBAYASHI, Atsushi HORIKAWA, Hitoshi FUJIWARA
  • Patent number: 8978384
    Abstract: A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.
    Type: Grant
    Filed: November 23, 2011
    Date of Patent: March 17, 2015
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Abdul Rafey Khan, Mohan Krishna Bobba
  • Patent number: 8973369
    Abstract: A gas-turbine burner having a plurality of main swirl generators which each have 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: December 14, 2012
    Date of Patent: March 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Robert Angel, Drew Ehlert, Matthias Hase, Michael Huth, James Marshall, Yevgeniy Shteyman
  • Patent number: 8966910
    Abstract: A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.
    Type: Grant
    Filed: June 21, 2011
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventors: Kevin Weston McMahan, Ronald James Chila, David Richard Johns
  • Patent number: 8966907
    Abstract: Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.
    Type: Grant
    Filed: April 16, 2012
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventors: Abdul Rafey Khan, Bradley Donald Crawley, Robert Joseph Rohrssen, Mohan Krishna Bobba
  • Patent number: 8966909
    Abstract: A system and method for reducing combustion dynamics includes first and second combustors arranged about an axis, and each combustor includes a plurality of tubes that extend axially through at least a portion of the combustor and a combustion chamber downstream from the plurality of tubes. A fuel injector extends through each tube to provide fluid communication into each tube at a fourth axial distance from the combustion chamber. The fourth axial distance in the first combustor is different than the fourth axial distance in the second combustor.
    Type: Grant
    Filed: August 21, 2012
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventors: Sarah Lori Crothers, Gilbert Otto Kraemer
  • Publication number: 20150052899
    Abstract: An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.
    Type: Application
    Filed: August 11, 2014
    Publication date: February 26, 2015
    Inventor: Ian James TOON
  • Publication number: 20150047360
    Abstract: A system for injecting a liquid fuel into a combustion gas flow field includes an annular liner that defines a combustion gas flow path. The annular liner includes an inner wall, an outer wall and a fuel injector opening that extends through the inner wall and the outer wall. The system further includes a gas fuel injector that is coaxially aligned with the fuel injector opening. The gas fuel injector includes an upstream end and a downstream end. The downstream end terminates substantially adjacent to the inner wall. A dilution air passage is at least partially defined by the gas fuel injector. A liquid fuel injector extends partially through the dilution air passage. The liquid fuel injector includes an injection end that terminates upstream from the inner wall.
    Type: Application
    Filed: August 13, 2013
    Publication date: February 19, 2015
    Applicant: General Electric Company
    Inventors: Abinash Baruah, Gilbert Otto Kraemer, Predrag Popovic, William Francis Carnell, JR.
  • Publication number: 20150047361
    Abstract: A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip.
    Type: Application
    Filed: January 27, 2014
    Publication date: February 19, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventors: Steven Williams, Timothy A. Fox, Reinhard Schilp
  • Publication number: 20150040571
    Abstract: A method for controlling fuel splits to a controller is provided that includes comparing a combustor operating parameter to a predefined combustor operating parameter range. If the combustor operating parameter is outside its respective range, then a modified turbine firing temperature is calculated. The modified turbine firing temperature may then be used to determine the fuel splits to the combustor using a nominal fuel splits lookup table.
    Type: Application
    Filed: August 7, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventor: Nilanjan Prosad Coomar
  • Patent number: 8950189
    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: Grant
    Filed: June 28, 2011
    Date of Patent: February 10, 2015
    Assignee: United Technologies Corporation
    Inventor: Timothy S. Snyder
  • Publication number: 20150033749
    Abstract: In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.
    Type: Application
    Filed: July 28, 2014
    Publication date: February 5, 2015
    Inventors: Ilya Aleksandrovich Slobodyanskiy, Lewis Berkley Davis, JR., Karl Dean Minto
  • Patent number: 8943831
    Abstract: The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles.
    Type: Grant
    Filed: June 22, 2011
    Date of Patent: February 3, 2015
    Assignee: Alstom Technology Ltd
    Inventors: Adnan Eroglu, Johannes Buss, Andrea Ciani
  • Patent number: 8938978
    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: Grant
    Filed: May 3, 2011
    Date of Patent: January 27, 2015
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Jonathan Dwight Berry, Luis Manuel Flamand, Kwanwoo Kim, Patrick Benedict Melton, Robert Joseph Rohrssen, John Drake Vanselow
  • Publication number: 20150020528
    Abstract: A fuel manifold and fuel injector arrangement for a gas turbine engine combustion chamber includes an annular combustion chamber casing arranged around the combustion chamber. Circumferentially spaced fuel injectors supply fuel into the combustion chamber and a fuel manifold supplies fuel to each of the fuel injectors. The fuel manifold includes flexible fuel pipes and a plurality of T piece connectors. The stem of each connector is mounted on an outer end of a respective one of the fuel feed arms and each flexible fuel pipe interconnects an arm of one connector with an arm of an adjacent connector. Each connector is arranged such that the arms are arranged are at angles to the planes containing the axis of the casing and perpendicular to the axis of the casing respectively. Adjacent connectors are arranged at opposite angles such that the fuel manifold extends around the casing sinusoidally.
    Type: Application
    Filed: June 24, 2014
    Publication date: January 22, 2015
    Inventor: Simon FULLER
  • Publication number: 20150007571
    Abstract: A combustor for a gas turbine that includes a front panel, an elongated sleeve with first end and second ends and a burner mounted in the sleeve. The second end of the sleeve seallessly mounted on the front panel. The sleeve and burner are configured to enable slidable mounted of the burner in the sleeve.
    Type: Application
    Filed: September 24, 2014
    Publication date: January 8, 2015
    Inventors: Ennio PASQUALOTTO, Jaan HELLAT, Pirmin SCHIESSEL
  • Patent number: 8925325
    Abstract: Combustion systems and the related methods operate to supply a stream of combustion products to a turbine in a gas turbine engine by forming an outer recirculation zone of recirculating combustion products within a combustor and by forming an inner recirculation zone inboard of the outer recirculation zone. The inner and outer recirculation zones are formed by imparting swirl to compressor discharge air passing through an outer air swirler and an inner air swirler radially inboard of the outer air swirler. Fuel is injected from an outer fuel injector into the outer recirculation zone, and fuel is also injected from an inner fuel injector into the inner recirculation zone.
    Type: Grant
    Filed: April 8, 2011
    Date of Patent: January 6, 2015
    Assignee: Delavan Inc.
    Inventors: Nicholas R. Overman, John Earl Short
  • Publication number: 20140366543
    Abstract: Combustion equipment for use in a gas turbine engine is provided. The combustion equipment includes an inner and outer case, wherein the outer case encloses the inner case creating a cavity located between the two cases. The combustion equipment also has a fuel delivery device for delivering fuel into a combustion region within the inner case, wherein the fuel delivery device passes through a hole in the outer case and a corresponding hole in the inner case. The combustion equipment also includes a seal assembly to prevent the leaking of pressurized gas into the cavity located between the outer and inner cases via the hole through which fuel delivery device passes. The seal assembly includes a flexible sleeve that extends around the fuel delivery device and interconnects the inner case with the outer case, permitting relative movement of the inner and outer cases when the combustion equipment is in use.
    Type: Application
    Filed: June 12, 2014
    Publication date: December 18, 2014
    Inventors: Jason Robert POTTS, Simon Mark JOLLIFF
  • Patent number: 8904796
    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: Grant
    Filed: October 19, 2011
    Date of Patent: December 9, 2014
    Assignee: General Electric Company
    Inventor: Arjun Singh
  • Publication number: 20140352321
    Abstract: A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine.
    Type: Application
    Filed: November 30, 2012
    Publication date: December 4, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: General Electric Company
  • Publication number: 20140345291
    Abstract: A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion toroid.
    Type: Application
    Filed: August 8, 2014
    Publication date: November 27, 2014
    Applicant: Power Generation Technologies Development Fund, L P
    Inventor: Ernst Bergen
  • Publication number: 20140338359
    Abstract: A combustor (10) includes a cap (16), a liner (20), a transition piece (24), and a combustion chamber (22) located downstream from the cap (16) and defined by the cap and liner. A secondary nozzle (40) circumferentially arranged around the liner (20) or transition piece (24) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding the center body, and an annular passage between the center body and the shroud. A method for supplying fuel to a combustor (10) includes flowing fuel through a primary nozzle radially disposed in a breech end of the combustor and flowing fuel through a secondary nozzle (40) circumferentially arranged around and passing through at least one of a liner (20) or a transition piece. The secondary nozzle (40) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body (44), and an annular passage between the center body and the shroud.
    Type: Application
    Filed: September 22, 2011
    Publication date: November 20, 2014
    Inventors: Almaz Kamilevich Valeev, James Harold Westmoreland, III, Keith C. Belsom, John Alfred Simo