With Attendant Coaxial Air Swirler Patents (Class 60/748)
  • Patent number: 10458654
    Abstract: The invention relates to an annular combustion chamber in a turbine engine, comprising two coaxial walls of revolution, one an internal wall (12) and the other an external wall (14), between which emerge fuel injectors (19) each engaged in centring means (36) which are moveable in the radial direction in support means (38), the chamber also comprising means (50, 68) of axial retention in the upstream direction of the centring means. According to the invention, the means of axial retention in the upstream direction are removably fixed to at least one of the internal (12) or external (14) walls of revolution.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: October 29, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Brice Le Pannerer, Laurent Bernard Cameriano, Pierre-François Simon Paul Pireyre
  • Patent number: 10436448
    Abstract: An injector includes a feed arm extending from an inlet fitting to a nozzle body opposite the inlet fitting. The nozzle body includes a spray outlet in fluid communication with the inlet fitting for issuing a spray of fluid supplied at the inlet fitting. The inlet fitting of the feed arm includes a receptacle therein for receiving a fluid supply manifold inside the inlet fitting of the feed arm.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: October 8, 2019
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Brett A. Pfeffer, Mark A. Caples, Daniel E. Bleeker
  • Patent number: 10385809
    Abstract: A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body has an air passage, a fuel circuit radially outboard from the air passage with respect to the longitudinal axis, and a cooling circuit. The fuel circuit extends from a fuel circuit inlet to a fuel circuit annular outlet. The fuel circuit is defined between a fuel circuit inner wall and a fuel circuit outer wall. At least a portion of the fuel circuit outer wall is radially outboard from the fuel circuit inner wall with respect to the longitudinal axis. A cooling circuit is defined within at least one of the fuel circuit inner wall or the fuel circuit outer wall. The cooling circuit extends from an axial position proximate the fuel circuit inlet to an axial position proximate the fuel circuit outlet.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: August 20, 2019
    Assignee: Delavan Inc.
    Inventor: Lev A. Prociw
  • Patent number: 10371382
    Abstract: Combustor assemblies having heat shields and features for attaching the heat shields are provided. For example, a combustor assembly includes a combustor dome defining an aperture, and a heat shield defining an opening and including a cup extending about the opening that extends toward the aperture of the combustor dome. The combustor assembly also includes a collar comprising a first piece and a second piece that each surround a portion of the heat shield cup. The collar may include a first arm, a second arm, and a body connecting the first and second arms such that the collar defines a recess between the first and second arms. The combustor assembly also may include an attachment piece with a flange that is positioned in the recess with a heat shield flange; the attachment piece attaches to the combustor dome to couple the heat shield and the combustor dome.
    Type: Grant
    Filed: September 30, 2016
    Date of Patent: August 6, 2019
    Assignee: General Electric Company
    Inventor: Donald Michael Corsmeier
  • Patent number: 10317083
    Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The lip generally increases in diameter as it extends downstream.
    Type: Grant
    Filed: October 3, 2014
    Date of Patent: June 11, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Yen-Wen Wang, Nigel Davenport, Eduardo Hawie
  • Patent number: 10253985
    Abstract: The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.
    Type: Grant
    Filed: February 22, 2016
    Date of Patent: April 9, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Michael Thomas Maurer, Jeffrey De Jonge, Felix Baumgartner, Patrik Meng
  • Patent number: 10215419
    Abstract: A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.
    Type: Grant
    Filed: July 8, 2016
    Date of Patent: February 26, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jakub Strzepek, Sri Sreekanth, Kian McCaldon, Honza Stastny, Dan Titirica
  • Patent number: 10208956
    Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: February 19, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Parham Zabeti
  • Patent number: 10209146
    Abstract: An apparatus and a process for experimentally determining a heat transfer coefficient of a surface which includes a duct having an outer passage for water flow and an inner passage for air flow, the two passages separated by a thin wall membrane such that the water flow establishes a datum temperature on the thin wall membrane, and where air flowing through the second passage and over the thin wall membrane surface which can include heat transfer enhancements features will be heated by the features, and where the heat transfer coefficient can be determined from the surface temperature of the thin wall membrane and the change in temperature of the air flow. The duct with the thin wall membrane and heat transfer enhancement features is produced using a plastic or metallic additive manufacture process for low cost and quit turnaround time.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: February 19, 2019
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC
    Inventors: Christopher K Rawlings, Phillip M Redman, Bryan C Bernier, James P Downs
  • Patent number: 10202861
    Abstract: A sealing arrangement for sealing a gap between two components which bear flat against one another on the gap side and which can be assembled only by transverse movement, wherein each component has a step on the gap side to form an overlapping stop and the steps are curved along their edges. One of the two components has a first groove which extends in a manner analogous to the curved edge and which is arranged in the set-back partial surface of the gap side of the component in question. The other of the two components has a recess located opposite the groove, and a modular sealing element comprising a sealing strip and a spiral strip is provided, which bears with its first sealing section, protruding from the groove, against a side face of the recess.
    Type: Grant
    Filed: January 19, 2015
    Date of Patent: February 12, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Berthold Vogel, Karl Klein, Stephan Sonnen
  • Patent number: 10197282
    Abstract: A multistaged lean prevaporizing premixing fuel injector apparatus is provided. The fuel injector may be utilized with a turbogenerator. Preheated combustion air from the turbogenerator's recuperator may be utilized by the fuel injector to prevaporize liquid fuel. The injector may provide for premixing of multiple fuel streams and include multiple stages with a flow distributor plate separating adjacent stages. The injector may include multiple stages, with a pilot tube located in a final stage splitting the fuel stream into a premixed pilot stream and a premixed final fuel and air mixture stream.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: February 5, 2019
    Assignee: Capstone Turbine Corporation
    Inventors: Mark G. Mitchell, Junhua Chen
  • Patent number: 10139108
    Abstract: A combustor basket assembly for a gas turbine engine that includes a combustor basket having a basket liner including an input end and an output end. An integrated exit cone and splash plate member is affixed to the output end of the basket liner and includes a base portion, an exit cone portion and a splash plate portion. The base portion includes an annular cooling channel that receives a cooling air flow and the exit cone portion and the splash plate portion each include an array of cooling feed holes in fluid communication with the cooling channel. The spacing between the feed holes and the size of the feed holes can be optimized to provide more cooling for hotter regions.
    Type: Grant
    Filed: June 8, 2015
    Date of Patent: November 27, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard L. Thackway, Charalambos Polyzopoulos, Jr., James M. Hurney
  • Patent number: 10101031
    Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.
    Type: Grant
    Filed: June 30, 2014
    Date of Patent: October 16, 2018
    Assignee: United Technologies Corporation
    Inventors: Alexander W. Williams, Seth A. Max, Christopher B. Lyons
  • Patent number: 10060622
    Abstract: The present invention relates to an axial swirler, in particular for premixing of oxidizer and fuel in gas turbines. The axial swirler for a gas turbine burner includes a plurality of swirl vanes with a streamline cross-section being arranged around a swirler axis and extending in radial direction between an inner radius Rmin and an outer radius Rmax. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. A discharge flow angle ? between a tangent to the swirl vane camber line at its trailing edge and the swirler axis is first function of radial distance R from the swirler axis. A position of maximum camber of the swirl vane is second function of radial distance R from the swirler axis. At least one swirl vane of the first and second functions include each a respective local maximum and local minimum values along said radial distance from Rmin to Rmax. The invention also relates to a burner with such a swirler.
    Type: Grant
    Filed: July 8, 2015
    Date of Patent: August 28, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Fernando Biagioli, Madhavan Narasimhan Poyyapakkam, Stefan Wysocki
  • Patent number: 10018167
    Abstract: A combustion chamber includes an upstream end wall having an aperture and a fuel injector. An air swirler is mounted such that the air swirler is movable radially with respect to the aperture. An inner wall of the air swirler has a first portion. A fuel injector head of the fuel injector is arranged coaxially within the air swirler. An outer wall of the fuel injector head has a first portion. The inner diameter of the first portion of the air swirler is less than the outer diameter of the first portion of the fuel injector head. One of the first portions is elastically radially deformable to allow the fuel injector head to be installed and removed from the air swirler. The inner wall and the outer wall have inter-engaging radially and axially extending faces to align the fuel injector head axially and radially within the air swirler.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: July 10, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Luca Tentorio
  • Patent number: 9958161
    Abstract: A gas turbine engine comprises an annular combustor chamber formed between an inner liner and an outer liner. An annular upstream zone is adapted to receive fuel and air from an annular nozzle. An annular mixing zone is located downstream of the upstream zone. The mixing zone has a reduced radial height relative a downstream combustion zone of the combustion chamber, the mixing zone defined by straight wall sections.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: May 1, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Tin Cheung John Hu
  • Patent number: 9957897
    Abstract: A gimbal tube system for an onboard injector (OBI) includes a transfer tube having a first transfer tube end that can be mounted to an inner diameter of a stator platform and a second transfer tube end defining a transfer tube pivot connector. The system also includes a gimbal tube including a first gimbal tube end that defines a gimbal tube pivot connector that can movably mount to the transfer tube pivot connector such that the gimbal tube and the transfer tube can move relative to each other at a pivot joint defined between the transfer tube and the gimbal tube. The gimbal tube further includes a second gimbal tube end defining a nozzle that can be inserted into the OBI.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: May 1, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas E. Clark, Jeffrey Vincent Anastas
  • Patent number: 9939157
    Abstract: A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: April 10, 2018
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Duane Douglas Thomsen
  • Patent number: 9927126
    Abstract: A pilot fuel injector is provided for a fuel nozzle of a gas turbine engine. The pilot fuel injector can include an axially-elongated, inner pilot centerbody wall extending from an upstream end to a downstream end, with the axially-elongated, inner pilot centerbody wall having a diverging-converging orientation with respect to a centerline axis to define a hollow tube having an upstream diameter, a throat, and a downstream diameter such that the throat has an inner diameter that is less than both of the upstream diameter and the downstream diameter. The pilot fuel injector also includes a center air circuit positioned at the upstream end, and an annular fuel passage defining the downstream end and intersecting with the centerbody wall at a pilot fuel metering orifice. A pilot fuel film surface is downstream from the annular fuel passage.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: March 27, 2018
    Assignee: General Electric Company
    Inventors: Michael Anthony Benjamin, Alfred Albert Mancini, Rameshkumar Muthuvel Chandrasekaran
  • Patent number: 9920693
    Abstract: A fuel injector component includes a body, an elongate void and a plurality of bores. The body has a first surface and a second surface. The elongate void is enclosed by the body and is integrally formed between portions of the body defining the first surface and the second surface. The plurality of bores extends into the second surface to intersect the elongate void. A process for making a fuel injector component includes building an injector component body having a void and a plurality of ports connected to the void using an additive manufacturing process that utilizes a powdered building material, and removing residual powdered building material from void through the plurality of ports.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: March 20, 2018
    Assignee: United Technologies Corporation
    Inventor: Russell B. Hanson
  • Patent number: 9709279
    Abstract: A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed in the first oxidant flow path. The second combustor includes a second oxidant flow path and a second perforated structure comprising a second plurality of oxidant ports. The second perforated structure is disposed in the second oxidant flow path and the first perforated structure has at least one difference relative to the second perforated structure.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: July 18, 2017
    Assignee: General Electric Company
    Inventors: Sarah Lori Crothers, Lucas John Stoia, William Francis Carnell, Jr.
  • Patent number: 9625152
    Abstract: A heat shield for a combustor of a gas turbine engine has a heat shield adapted to be mounted to a combustor wall with a back face of the heat shield in spaced-apart facing relationship with an inner surface of the combustor wall to define an air gap. Rails extend from the back face of the heat shield across the air gap. Grooves are defined in at least one of the rails. The rail grooves are in fluid flow communication with the air gap when the heat shield is mounted to the combustor wall.
    Type: Grant
    Filed: June 3, 2014
    Date of Patent: April 18, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Papple, Robert Sze
  • Patent number: 9599022
    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: Grant
    Filed: January 30, 2013
    Date of Patent: March 21, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Bhawan B Patel, John Greer, Parthasarathy Sampath
  • Patent number: 9592480
    Abstract: An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface.
    Type: Grant
    Filed: May 13, 2013
    Date of Patent: March 14, 2017
    Assignee: Solar Turbines Incorporated
    Inventors: Donald James Cramb, James Scott Piper, Sean Kelly Spivey, Michael John Ramotowski, Matthew Mayer
  • Patent number: 9506352
    Abstract: The present invention relates to a turbine blade of a gas turbine with an airfoil arranged on a blade root and having at least one cooling air duct running in the longitudinal direction of the turbine blade, arranged inside the turbine blade and extending through the blade root, characterized in that at least one swirl-generating element is arranged in the transitional area between blade root and airfoil in the cooling air duct, with the swirl-generating element including an outer ring and several swirl-generating stator vanes arranged thereon, which are connected to a centric area, as well as to a method for its manufacture.
    Type: Grant
    Filed: September 3, 2013
    Date of Patent: November 29, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Knut Lehmann, Tijana Filipova
  • Patent number: 9500371
    Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.
    Type: Grant
    Filed: February 8, 2013
    Date of Patent: November 22, 2016
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Frederic Marius Mathieu, Gilles Ulryck
  • Patent number: 9476429
    Abstract: A feed diffuser is disclosed. The diffuser may comprise a base disposed orthogonal to a flow, a body extending from the base toward the flow, and an apex provided at a termination of the body in a direction toward the flow. The body may decrease in cross-sectional area from the base to the apex.
    Type: Grant
    Filed: December 19, 2012
    Date of Patent: October 25, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Brian Beach
  • Patent number: 9447974
    Abstract: The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirl assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.
    Type: Grant
    Filed: September 13, 2012
    Date of Patent: September 20, 2016
    Assignee: United Technologies Corporation
    Inventors: Seth A. Max, Jonathan M. Jause
  • Patent number: 9447976
    Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas gallery and a gas passage. The gas gallery is an annular passage configured to circumferentially distribute gas fuel. The gas passage includes an inlet and an outlet. The inlet is distal to the gas gallery and includes an inlet area with a circular shape. The outlet adjoins the gas gallery and includes an outlet area including an annular sector shape. The gas passage is configured to diffuse the gas fuel and discharge the gas fuel from the outlet and into the gas gallery.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: September 20, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: Christopher Zdzislaw Twardochleb, Rasoul Z. Paydar
  • Patent number: 9429042
    Abstract: An acoustic damping device is provided which includes at least one opening for a sealing gas to deflect a grazing gas flow away from the mouth of an acoustic damper.
    Type: Grant
    Filed: February 26, 2015
    Date of Patent: August 30, 2016
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Franklin Marie Genin, Devis Tonon, Mirko Ruben Bothien, Douglas Anthony Pennell
  • Patent number: 9360218
    Abstract: A fuel injection device is provided. The device includes a pilot injector opening out into a venturi and an annular row of multipoint injection orifices opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall. The outer peripheral edge of the separation wall has a diameter greater than the diameter of the annular row of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.
    Type: Grant
    Filed: September 27, 2013
    Date of Patent: June 7, 2016
    Assignee: SNECMA
    Inventors: Matthieu Francois Rullaud, Galadriel Dancie, Romain Nicolas Lunel, Thomas Olivier Marie Noel
  • Patent number: 9347378
    Abstract: A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.
    Type: Grant
    Filed: May 13, 2013
    Date of Patent: May 24, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: Donald James Cramb, James Scott Piper, Sean Kelly Spivey, Michael John Ramotowski, Matthew Mayer
  • Patent number: 9322555
    Abstract: A cap assembly for a bundled tube fuel injector includes an impingement plate and an aft plate that is disposed downstream from the impingement plate. The aft plate includes a forward side that is axially separated from an aft side. A tube passage extends through the impingement plate and the aft plate. A tube sleeve extends through the impingement plate within the tube passage towards the aft plate. The tube sleeve includes a flange at a forward end and an aft end that is axially separated from the forward end. A retention plate is positioned upstream from the impingement plate. A spring is disposed between the retention plate and the flange. The spring provides a force so as to maintain contact between at least a portion of the aft end of the tube sleeve and the forward side of the aft plate.
    Type: Grant
    Filed: July 1, 2013
    Date of Patent: April 26, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jeffrey Scott LeBegue, Patrick Benedict Melton, James Harold Westmoreland, III, James Scott Flanagan
  • Patent number: 9322554
    Abstract: A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.
    Type: Grant
    Filed: July 29, 2011
    Date of Patent: April 26, 2016
    Assignee: United Technologies Corporation
    Inventors: Won-Wook Kim, James B. Hoke, Timothy S. Snyder
  • Patent number: 9316411
    Abstract: A heating, ventilation, and/or air conditioning (HVAC) furnace has a flat burner comprising an upstream side and a downstream side, the flat burner being configured to receive an air-fuel mixture therethrough, a first flow path located adjacent the flat burner and downstream relative to the flat burner, the first flow path configured to receive fluid exiting the flat burner, and a plurality of second flow paths located downstream relative to the first flow path, the plurality of second flow paths being configured to receive fluid from the first flow path.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: April 19, 2016
    Assignee: Trane International Inc.
    Inventors: Lester D. Sherrow, Nancy Souvoravong, Jeffery Wayne O'Daniel
  • Patent number: 9267688
    Abstract: A head part of an annular combustion chamber for a gas turbine, the head part comprising: an end wall with a passage opening for accommodating a burner, the end wall comprising a back side which faces towards the combustion chamber; a burner collar adapted to fit within the passage opening and receive the burner, the burner collar comprising a protruding portion radially protruding from an outer surface of the burner collar; and a ring member for receiving the protruding portion of the burner collar; wherein the head part of the annular combustion chamber is configured such that in an installed configuration a radially outer portion of the ring member engages with the end wall and a radially inner portion of the ring member receives the protruding portion of the burner collar.
    Type: Grant
    Filed: April 19, 2012
    Date of Patent: February 23, 2016
    Assignee: ROLLS-ROYCE plc
    Inventor: Richard G. Milburn
  • Patent number: 9228747
    Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: January 5, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Parham Zabeti
  • Patent number: 9127843
    Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: September 8, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
  • Patent number: 9027350
    Abstract: A gas turbine engine including a combustor with a combustion liner having inner and outer walls is disclosed herein. The gas turbine engine further includes a swirler system adapted to receive a fuel injector and a flow splitter operable to bifurcate an airflow exiting the swirler system into a first bifurcated flow and a second bifurcated flow. A shroud is positioned downstream of the flow splitter and is configured to deflect the first bifurcated flow in a first direction radially inward and the second bifurcated flow in a second direction radially outward. The second bifurcated flow cools both of the inner and outer walls of the combustor liner.
    Type: Grant
    Filed: October 26, 2010
    Date of Patent: May 12, 2015
    Assignee: Rolls-Royce Corporation
    Inventor: Timothy Carl Roesler
  • Patent number: 9021811
    Abstract: A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes positioned radially around a central axis of the swirler and a plurality of mixing channels for mixing the fuel and the air. At least one mixing channel of the plurality of mixing channels is defined by opposite walls of two adjacent vanes of the plurality of vanes and is comprising at least one fuel injection opening and is further comprising at least one dimple for generating a vortex of the air. Further, a combustion chamber incorporating such a swirler and a gas turbine incorporating such a combustion chamber are provided.
    Type: Grant
    Filed: May 5, 2009
    Date of Patent: May 5, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventor: Kam-Kei Lam
  • Patent number: 9021781
    Abstract: A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged.
    Type: Grant
    Filed: January 4, 2013
    Date of Patent: May 5, 2015
    Assignee: General Electric Company
    Inventors: Kaitlin Marie Graham, James Scott Flanagan, Jeffrey Scott LeBegue
  • Patent number: 9021812
    Abstract: A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.
    Type: Grant
    Filed: July 27, 2012
    Date of Patent: May 5, 2015
    Assignee: Honeywell International Inc.
    Inventors: Ronald B. Pardington, Paul Yankowich, Nagaraja S. Rudrapatna, Thomas Frank Johnson
  • Publication number: 20150113993
    Abstract: A fuel injector assembly includes a fuel injector and a fuel injector shroud housing the fuel injector. The fuel injector includes a body and a nozzle coupled to the body. The fuel injector shroud includes a swirler device defining a center opening proximate to the nozzle of the fuel injector and a plurality of swirler holes surrounding the center opening, a body section with an air inlet configured to admit a flow of air into the fuel injector shroud and a dome section defining a mount for securing the swirler device to the body section, and at least one interior rib positioned on an interior surface of the dome section configured to direct the flow of air to the swirler holes of the swirler device such that the flow of air exiting through the swirler is mixed with the flow of fuel exiting the nozzle.
    Type: Application
    Filed: October 30, 2013
    Publication date: April 30, 2015
    Inventors: Nagaraja S. Rudrapatna, Thomas J. Bronson, Donald G. Godfrey
  • 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: 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: 8991187
    Abstract: The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.
    Type: Grant
    Filed: October 11, 2010
    Date of Patent: March 31, 2015
    Assignee: General Electric Company
    Inventors: Michael John Hughes, Jonathan Dwight Berry, Jason Thurman Stewart, Almaz Valeev, Chunyang Wu
  • 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
  • Patent number: 8984889
    Abstract: A combustor for a gas-turbine engine including a burner head, a combustion chamber disposed downstream of the burner head, a swirler for creating a swirling flow of air in the combustion chamber, and a fuel nozzle disposed in the burner head. The fuel nozzle is disposed giving rise to a first angle of exit of the fuel from a downstream face of the burner head of >±0° with respect to a longitudinal axis of the combustor, this first angle lying in a first plane passing through the longitudinal axis. The fuel also exits at a second angle from the downstream face of >±0° with respect to the first plane, the second angle lying in a second plane orthogonal to the first plane.
    Type: Grant
    Filed: October 8, 2008
    Date of Patent: March 24, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventor: Nigel Wilbraham
  • 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