With Fuel Injector Patents (Class 60/740)
  • Patent number: 11125436
    Abstract: A floating collar assembly is configured to receive a fuel nozzle or an igniter projecting through an opening defined in a combustor shell lined with heat shields having studs projecting through the combustor shell for engagement with corresponding fasteners outside the combustor shell. A floating collar is mounted outside the combustor shell with an opening in alignment with the opening in the combustor shell for receiving the fuel nozzle or the igniter. An external retaining bracket is mounted to the heat shield studs or other studs projecting outwardly from the combustor shell so as to trap the floating collar between the combustor shell and the bracket.
    Type: Grant
    Filed: July 3, 2019
    Date of Patent: September 21, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Maximilian Baranowicz, Si-Man Amy Lao, Oleg Morenko
  • Patent number: 11079112
    Abstract: In a combustor, and in a gas turbine including the same, a path in which compressed air is mixed with fuel may be increased in each of a plurality of main nozzles. The combustor includes a nozzle casing axially extending in parallel with an extension line (PL); and a plurality of main nozzles to mix and inject compressed air and fuel, the plurality of main nozzles arranged inside the nozzle casing along an imaginary annular line, at least one main nozzle having a center axis inclined at a predetermined angle with respect to the extension line. A central nozzle surrounded by the main nozzles may be disposed in the nozzle casing so as to be parallel to the extension line. Thus, the at least one main nozzle has a path in which the fuel and the compressed air flow that is longer than in the central nozzle.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: August 3, 2021
    Inventor: Jaewon Seo
  • Patent number: 11029031
    Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, and a rail disposed about a periphery of the cold side, the rail including a first rail member having a first length extending along the panel, a first height extending from the cold side, and a first thickness that varies along the first length.
    Type: Grant
    Filed: August 2, 2018
    Date of Patent: June 8, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Jon E. Sobanski, Steven D. Porter
  • Patent number: 11029029
    Abstract: A fuel injector heat exchanger assembly is provided, in which the fuel injector assembly includes a body defining an outer surface and an inner surface. The body includes a plurality of walls in concentric arrangement. The plurality of walls defines a plurality of passages including a first passage surrounded by a second passage, and a third passage surrounding the second passage. Each passage is fluidly segregated from one another by the plurality of walls. A first conduit wall is defined through the body from the outer surface. The first conduit wall defines a first conduit in fluid communication with the second passage. The first conduit wall fluidly segregates the first conduit from the third passage. The first conduit is configured to admit a flow of fluid from outside the fuel injector into the second passage.
    Type: Grant
    Filed: January 3, 2019
    Date of Patent: June 8, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Varun Swaminathan Lakshmanan, Michael Anthony Benjamin, Veeraraju Vanapalli, Karthikeyan Sampath
  • Patent number: 10982856
    Abstract: A fuel nozzle for injecting fuel and air into a combustor of a gas turbine engine, the fuel nozzle comprising: an outer component having an outward surface adapted for exposure to a flow of hot gas within the combustor, and an inward surface; an inner component concentrically disposed within the inward surface of outer component along a nozzle axis, the inner component defining an axially extending air flow channel; an air passage bore extending through the outward surface of the outer component and communicating with the air flow channel; and a thermal insulating sleeve disposed within the air passage bore, the sleeve having a sleeve body spaced apart from the outer component by an air gap.
    Type: Grant
    Filed: February 1, 2019
    Date of Patent: April 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Saeid Oskooei, Gavin Rohiteswar Kisun, Nadia Cheri Swaby, Roger Neil Antony Francis
  • Patent number: 10907831
    Abstract: A fuel injection system may include a fuel spray nozzle including a nozzle head and a nozzle stem. The nozzle head may include an air channel and a swirler in fluid communication with the air channel. The nozzle stem may extend into a compressor discharge pressure cavity and convey fuel to the air channel. The air channel may combine air from the swirler with the fuel from the nozzle stem and convey a mixture of fuel and air to a combustor. The fuel injection system may further include a scoop. The scoop may be coupled to the fuel spray nozzle. The scoop may receive air that flows into the compressor discharge pressure cavity from a diffusor. An outer surface of the fuel spray nozzle and an inner surface of the scoop define a duct in fluid communication with the swirler. The swirler may receive air from the duct.
    Type: Grant
    Filed: May 7, 2018
    Date of Patent: February 2, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Jack D. Petty, Sr., John Holdcraft, Kevin Sauer
  • Patent number: 10871287
    Abstract: A burner for a rotary kiln comprising an elongated tubular body (6) having a longitudinal axis (L) and a discharge end (7) adjacent a combustion zone comprising a flame, at least one fuel supply pipe for transporting and ejecting fuel through a fuel pipe outlet (10) at the discharge end (7), the fuel being alternative fuel or a mixture of alternative fuel and fossil fuel, and at the discharge end (7), a number of high speed primary air jet outlets for ejecting primary air and being arranged, when seen towards the discharge end, along a closed line, such as a circle, outwardly of the fuel outlet (10) and surrounding the fuel outlet, wherein at least one of the primary air outlets and preferably a number of the primary air outlets comprise a single orifice outlet or a multiple orifice outlet forming a flat jet air outlet (11) having a major axis and a minor axis and being configured to eject a flat jet air stream (13) having a flat fan pattern with a predetermined fan angle v.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: December 22, 2020
    Inventors: Mads Nielsen, Morten Drivsholm, Linda Kaare Norskov
  • Patent number: 10865986
    Abstract: A vortex generating device is provided as a generally airfoil-shaped lobed body. The flow deflection varies along a spanwise extent, such that the body exhibits a corrugated geometry in a trailing edge region, and the trailing edge exhibits an undulating shape. The undulating shape includes at least one corner. The trailing edge may include or may consist of straight trailing edge sections. The trailing edge may exhibit a polygonial waveform shape, in particular a trapezoidal or rectangular waveform shape. The vortex generating device may be provided as a fuel discharge device which is suited to discharge a fuel into a vortex flow generated by the vortex generating device. To this extent, a fuel supply plenum may be provided inside the body and at least one fuel discharge opening which is in fluid communication with the fuel supply plenum may be provided on the trailing edge.
    Type: Grant
    Filed: November 29, 2017
    Date of Patent: December 15, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Andre Theuer, Urs Benz, Yang Yang, Michael Düsing
  • Patent number: 10865714
    Abstract: The subject matter of this specification can be embodied in, among other things, a fuel injector for a gas turbine engine includes a fuel injector housing, and an elongated fuel tube held in position in said housing by spaced apart joints and including an undulating tube surface along at least a portion of its length between said joints, said undulating tube surface being in contact with another surface disposed in said housing at one or more locations of said undulating tube surface.
    Type: Grant
    Filed: March 22, 2018
    Date of Patent: December 15, 2020
    Assignee: Woodward. Inc.
    Inventors: Mark G. Goeddeke, Michael Stratton
  • Patent number: 10865992
    Abstract: A fuel injector is provided for the radial introduction of a fuel/air mixture to a combustor. The fuel injector includes a frame having interior sides defining an opening for passage of a first fluid; at least one fuel injection body; and a conduit fitting. The at least one fuel injection body is coupled to the frame and positioned within the opening, thereby defining flow paths for the first fluid. The at least one fuel injection body defines a fuel plenum, and a set of fuel injection holes are defined through an outer surface of the at least one fuel injection body. The conduit fitting is coupled to the frame and conveys fuel from a fuel supply line to the fuel plenum. Fuel and the first fluid mix in the flow paths and are delivered through the outlet to the combustor.
    Type: Grant
    Filed: December 30, 2016
    Date of Patent: December 15, 2020
    Assignee: General Electric Company
    Inventors: Richard Martin DiCintio, Seth Reynolds Hoffman, Ronnie Ray Pentecost, Jayaprakash Natarajan, Wei Zhao
  • Patent number: 10851996
    Abstract: Heat shields and methods of cooling a heat shield are provided. A heat shield of a combustor may be cooled. The heat shield comprises a first surface and a second surface, where the first surface is opposite the second surface, and the first surface is configured to face a combustion chamber. The heat shield may be cooled by directing airflow over the heat shield through channels towards an opening of the heat shield and past turbulators located in the channels.
    Type: Grant
    Filed: July 6, 2018
    Date of Patent: December 1, 2020
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventor: Christopher Dwayne DeBruhl
  • Patent number: 10837364
    Abstract: A gas turbine engine comprises a fan delivering air into a bypass duct as bypass air and into a core engine. The core engine includes a high pressure compressor, a combustor, and a turbine section including a fan drive turbine driving a fan rotor through a gear reduction. The high pressure compressor having a downstream most location and air in a chamber radially outward of the combustor being air downstream of the downstream most location in the high pressure compressor. A tap taps compressed air and moves compressed air through a heat exchanger, then returns the compressed air back into a core engine housing and passes the returned air through a conduit radially outwardly of the combustor. The air is passed from the conduit radially inwardly to cool the turbine section.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: November 17, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Gary D. Roberge
  • Patent number: 10816207
    Abstract: A fuel nozzle for a gas turbine engine includes a stem having a monolithic stem body extending longitudinally between a first end and a second end. The monolithic stem body has a radially outer surface and at least one helical fuel passage extending through the monolithic stem body and disposed inwardly from the radial outer surface. The at least one helical fuel passage extends helically through the monolithic stem body about a passage axis extending between the first and second ends.
    Type: Grant
    Filed: February 14, 2018
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michael A. Fryer
  • Patent number: 10816199
    Abstract: Combustor assemblies and combustor heat shields are provided. As one example, a combustor assembly comprises a flow path assembly including an outer wall, an inner wall, and a combustor dome that define a combustion chamber and are formed from a ceramic matrix composite (CMC) material. The combustor dome defines a plurality of dome openings, and a heat shield is positioned between the combustor dome and the combustion chamber that comprises a plurality of heat shield segments. Each heat shield segment defines a heat shield aperture that is aligned with a dome opening, and an aft surface of each segment is concave and a forward surface of each segment is convex. One of a plurality of fuel-air mixers is positioned through each heat shield aperture and dome opening, and one collar of a plurality of collars extends through each heat shield aperture to couple the heat shield to the fuel-air mixer.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventor: Donald Michael Corsmeier
  • Patent number: 10808623
    Abstract: A combustion chamber assembly, with a combustion chamber nozzle for providing a fuel-air mixture at a nozzle exit opening. A nozzle main body includes an inner air guiding channel for conveying air to the exit opening, a fuel guiding channel for conveying fuel to the exit opening that is positioned radially further outwards to the axis than the inner air guiding channel, and a radially outwardly positioned air guiding element for guiding the air and the fuel-air mixture discharged at the exit opening in a radially outwardly oriented outflow direction. A guide flow generation device creates a guide flow of air that radially borders the air and the fuel-air mixture discharged at the exit opening, and defines a maximum outflow angle for the outflow direction with respect to the nozzle longitudinal axis at which the air and fuel-air mixture discharged at the exit opening can flow radially outwards.
    Type: Grant
    Filed: March 13, 2019
    Date of Patent: October 20, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Max Staufer
  • Patent number: 10808934
    Abstract: A fuel injector for a gas turbine engine including an outer sleeve. An upstream end of the outer sleeve defines an inlet opening and a downstream end defines an exit opening, each of which defined within the outer sleeve. The outer sleeve defines a radial opening extended therethrough along the radial direction. At least a portion of the outer sleeve defines a plurality of grooves. The outer sleeve defines a fuel conduit through at least a portion of the outer sleeve outward of the plurality of grooves along the radial direction from the fuel injector centerline. The fuel conduit defines a fuel injection opening inward along the radial direction of the radial opening defined through the outer sleeve. A first member of an arm is coupled to the outer sleeve. A second member of the arm is contoured defining a fuel injection port generally concentric to the fuel injector centerline.
    Type: Grant
    Filed: January 9, 2018
    Date of Patent: October 20, 2020
    Assignee: General Electric Company
    Inventors: Gregory Allen Boardman, Jeffrey Michael Martini, Michael Anthony Benjamin, Pradeep Naik
  • Patent number: 10775048
    Abstract: A fuel nozzle for a gas turbine engine includes an outer body extending generally along a centerline axis and defining a plurality of openings in an exterior surface. The fuel nozzle additionally includes a main injection ring disposed at least partially inside the outer body, the main injection ring including a fuel post extending into or through one of the plurality of openings of the outer body. The fuel post defines a spray well and a main fuel orifice, the spray well defining a bottom surface, a side wall, and a taper in the bottom surface extending from the main fuel orifice towards the side wall.
    Type: Grant
    Filed: March 15, 2017
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Alfred Albert Mancini, Duane Douglas Thomsen
  • Patent number: 10753614
    Abstract: A fuel injector provided for gas turbine engine has a nozzle including pilot fuel and mains fuel discharge orifice's for respectively spraying pilot and mains fuel flows into a combustor of the engine. The injector further has a feed arm extending to the nozzle for feeding fuel to the pilot and mains discharge orifices from pilot and mains supplies respectively. The nozzle and the feed arm contain one or more pilot passages for flow of the pilot fuel flow from the pilot supply to the pilot discharge orifice and one or more mains passages for flow of the mains fuel flow from the mains supply to the mains discharge orifice. The nozzle and the feed arm contain a plurality of the pilot passages and/or a plurality of the mains passages. The pilot and the mains passages intertwine repeatedly, and are both smoothly curved as they intertwine around each other.
    Type: Grant
    Filed: March 16, 2018
    Date of Patent: August 25, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian M Garry, Mark Glover, Richard Mellor, Frederic Witham
  • Patent number: 10746101
    Abstract: An annular fuel manifold includes an annular fuel plenum defined within the annular fuel manifold, an axial inlet into the annular fuel plenum, and a deflector downstream of the axial inlet, the deflector oriented such that fluid flow into the annular fuel plenum from the axial inlet is deflected by the deflector at least partially along a circumference of the annular fuel plenum.
    Type: Grant
    Filed: June 13, 2017
    Date of Patent: August 18, 2020
    Assignee: General Electric Company
    Inventors: Thomas Edward Johnson, Kaitlin Marie Graham, Geoffrey David Myers
  • Patent number: 10724740
    Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: July 28, 2020
    Assignee: General Electric Company
    Inventors: Gregory Allen Boardman, Marco Venturato, Douglas Downey Turner, Valeria Proano Cadena, William Thomas Bennett
  • Patent number: 10704517
    Abstract: A combustion chamber comprising an upstream end wall, at least one annular wall, at least one fuel injector and at least one seal. The at least one annular wall being secured to the upstream end wall. The upstream end wall having at least one aperture. Each fuel injector being arranged in a corresponding one of the apertures in the upstream end wall and each seal being arranged in a corresponding one of the apertures in the upstream end wall and around the corresponding one of the fuel injectors. Each seal having an inner surface facing the corresponding one of the fuel injectors and an outer surface facing away from the corresponding one of the fuel injectors. Each seal abutting the corresponding one of the fuel injectors. The downstream end of each seal increasing in diameter in a downstream direction and the upstream end of each seal having a radially extending flange.
    Type: Grant
    Filed: December 11, 2017
    Date of Patent: July 7, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventors: David P. Wilson, John E. Rimmer, Jochen Rupp, Damian Martin, Emmanuel V. Aurifeille, Kyriakoulis L. Resvanis, Michael J. Allitt
  • Patent number: 10690107
    Abstract: An igniter for a dual fuel engine includes a plurality of spray orifices formed in a nozzle and defining a plurality of spray axes. A plurality of spark electrodes are resident on the nozzle and form spark gaps offset from the spray axes, in a spark gap pattern that is at variance in at least one of a circumferential aspect or an axial aspect with the spray plume pattern.
    Type: Grant
    Filed: February 18, 2019
    Date of Patent: June 23, 2020
    Assignee: Caterpillar Inc.
    Inventors: Jonathan W. Anders, Bobby John
  • Patent number: 10670018
    Abstract: A liquid injection apparatus for use with a compressor having a rotor shaft and a casing part is provided. The liquid injection apparatus includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.
    Type: Grant
    Filed: May 2, 2017
    Date of Patent: June 2, 2020
    Assignee: General Electric Company
    Inventors: Laxmikant Merchant, Valery Ivanovich Ponyavin, Jeffrey Patrick Mills, Divya Reddy Kothakapu, Weilun Yu, Joshua Adam Bagwell
  • Patent number: 10648673
    Abstract: A combustor includes a combustion tube having a cylindrical shape with a combustion space where fuel is combusted and including an inlet through which the fuel is introduced, an outlet through which a gas generated when the fuel is combusted is discharged, and a protrusion protruding inward from a wall surface between the inlet and the outlet; an injection unit configured to inject fuel into the combustion tube through the inlet of the combustion tube; and an additional injection unit located on the protrusion of the combustion tube and configured to inject fuel into the combustion tube.
    Type: Grant
    Filed: October 13, 2015
    Date of Patent: May 12, 2020
    Assignee: HANWHA AEROSPACE CO., LTD.
    Inventor: Ik Soo Kim
  • Patent number: 10570821
    Abstract: A pre-film liquid fuel cartridge includes a main body having a water passage, a liquid fuel passage, a compressed air passage and a pre-film tip disposed at a downstream portion of the pre-film liquid fuel cartridge. The pre-film tip includes a forward end portion that is axially separated from an aft end portion and an inner side that extends therebetween. The inner side at least partially defines a pre-filming surface which terminates at an emulsion atomizing shear edge. The pre-film tip includes a plurality of water injection ports oriented tangentially through the pre-filming surface, a plurality of liquid fuel injection ports oriented tangentially through the pre-filming surface and a plurality of atomizing air injection ports axially oriented around the emulsion atomizing shear edge. An atomizing air shear edge is defined downstream from the emulsion atomizing shear edge and the atomizing air injection ports.
    Type: Grant
    Filed: April 4, 2014
    Date of Patent: February 25, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Borys Borysovych Shershnyov, Alexey Yurievich Gerasimov
  • Patent number: 10539328
    Abstract: A nozzle guide support device, that supports a nozzle guide of a fuel nozzle on an open flange part encircling a fuel supply hole of a combustor of a gas turbine engine, is formed by fixing a cap that supports the nozzle guide in a floating state to the open flange part by means of a rivet. Rotation of the nozzle guide relative to the open flange part is restricted by engagement between a recess portion of the nozzle guide and a spacer fitted to the rivet. Accordingly, not only is it possible to cut production time and production cost compared with a case in which the nozzle guide support device is fixed by welding or brazing, but it is also possible to suppress unlimited rotation of the fuel nozzle guide while enabling the fuel nozzle guide to float in a radial direction and a axial direction.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: January 21, 2020
    Assignee: HONDA MOTOR CO., LTD.
    Inventors: Yasuharu Kamoi, Takeshi Kiyama
  • Patent number: 10508759
    Abstract: A flowpath assembly has a first conduit defining a flowpath radially inward, and a second conduit spaced radially outward from the first conduit. A void defined between the first and second conduits contains an insulating material that may have a greater porosity than the first and second conduits. The assembly may be additive manufactured generally as one unitary piece with the raw material of the conduits being melted and solidified on a slice-by-slice basis and the insulating material being selectively bypassed by an energy gun of an additive manufacturing system.
    Type: Grant
    Filed: July 27, 2017
    Date of Patent: December 17, 2019
    Assignee: United Technologies Corporation
    Inventors: Joe Ott, John J. Rup, Jr., Shawn Stempinski, Stanley J. Funk, Dennis M. Moura, Lexia Kironn, Roger O. Coffey
  • Patent number: 10495312
    Abstract: An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.
    Type: Grant
    Filed: January 18, 2016
    Date of Patent: December 3, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jose Roland Rodrigues, Christophe Chabaille
  • Patent number: 10495310
    Abstract: Combustor assemblies are provided. For example, a combustor assembly includes a combustor liner defining a combustion chamber and an annular combustor dome positioned at a forward end of the combustor liner that defines a plurality of dome apertures. The combustor assembly further includes an annular heat shield positioned between the combustor dome and the combustion chamber, a plurality of adapters positioned forward of the heat shield, and a plurality of collars. The heat shield defines a plurality of heat shield apertures that are aligned with the dome apertures. One adapter is attached to the combustor dome at each dome aperture, and the adapters are. One collar extends through each heat shield aperture to couple the heat shield to the combustor dome. Further, ceramic matrix composite (CMC) heat shields are provided that may include an annular body defining a plurality of heat shield apertures, as well as inner and outer wings.
    Type: Grant
    Filed: September 30, 2016
    Date of Patent: December 3, 2019
    Assignee: General Electric Company
    Inventor: Donald Michael Corsmeier
  • Patent number: 10488049
    Abstract: The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by an annular chamber end wall (48), said chamber comprising deflectors (50) mounted upstream of the annular chamber end wall (48). Injectors (19) are mounted in sleeves (44) at least one of which comprises a radially annular flange (66) which is designed to slide radially between the chamber end wall (48) and the deflector (50) and which is blocked axially between the chamber end wall (48) and the deflector (50).
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: November 26, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Romain Nicolas Lunel, Thomas Olivier Marie Noel, Matthieu François Rullaud
  • Patent number: 10309654
    Abstract: In a structure for cooling a gas turbine engine, an open flange part encircling a fuel supply hole formed in a combustor includes a conical portion enlarging in a conical shape toward an outside of the combustor and a flat portion extending radially outward in a flat plate shape from an extremity of the conical portion, and a nozzle guide includes a cylindrical portion covering an outer periphery of a fuel nozzle for supplying fuel to the fuel supply hole and a bottom flange portion being bent radially outward from a corner portion at an extremity of the cylindrical portion and supported in a floating state on the flat portion. A cooling hole for supplying air that cools the open flange part and the nozzle is formed in the corner portion of the guide, and a direction of the cooling hole is inclined toward an axis of the nozzle.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: June 4, 2019
    Assignee: HONDA MOTOR CO., LTD.
    Inventors: Yasuharu Kamoi, Daisuke Kato
  • Patent number: 10294865
    Abstract: A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: May 21, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Patent number: 10253976
    Abstract: A fuel swirler with anti-rotation features is provided. A swirler assembly may comprise a swirler, a guide plate, and a retaining ring. The swirler, the guide plate, and/or the retaining ring may comprise recessions configured to receive a retaining element. The retaining element may be configured to interface with the recessions to create an interference in the swirler assembly. The interference may at least partially resist rotation of the guide plate with respect to the swirler.
    Type: Grant
    Filed: April 24, 2017
    Date of Patent: April 9, 2019
    Assignee: United Technologies Corporation
    Inventor: Peter E. Gunderson
  • Patent number: 10190776
    Abstract: A fuel injector system with a fuel feed arm extending inwardly from an outer casing of combustion equipment of a gas turbine engine to a flame tube of the equipment, which ends in an injection nozzle which penetrates a head of the tube to deliver fuel. The system has a swirler arranged coaxially with the nozzle at the head of the tube, including one or more circuits which produce flows of swirling air around the fuel. A seal ring seals the nozzle to the swirler, the nozzle being removably inserted into the ring. The ring has a flange portion, and the swirler has a pair of spaced retention grooves at a front face thereof. Opposite edges of the flange portion slidingly locate in the grooves so it sealingly engages to the front face. The swirler has a spring mechanism which retains the flange portion in the grooves.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: January 29, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Alan Geary, Keith Bell
  • Patent number: 10174946
    Abstract: A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: January 8, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frank J. Cunha, Stanislav Kostka
  • Patent number: 10151485
    Abstract: A turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: December 11, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Nicolas Lunel, Denis Jean Maurice Sandelis
  • Patent number: 10082082
    Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes a flange assembly with a distribution block, three main gas tubes, and an injector head. The distribution block evenly distributes a main gas fuel to the three main gas tubes. The injector head includes an injector body with a primary gas gallery including an annular shape. The three main gas tubes are connected in a parallel configuration between the distribution block and the primary gas gallery. The three main gas tubes are all in flow communication with the primary gas gallery and provide the main gas fuel from the same main gas fuel source.
    Type: Grant
    Filed: January 5, 2016
    Date of Patent: September 25, 2018
    Assignee: Solar Turbines Incorporated
    Inventors: Sean Kelly Spivey, Donald James Cramb, James Scott Piper, Michael John Ramotowski
  • Patent number: 10072845
    Abstract: An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.
    Type: Grant
    Filed: November 15, 2013
    Date of Patent: September 11, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Joshua Tyler Mook, Michael Anthony Benjamin, David Richard Barnhart, Sean James Henderson, Ramon Martinez, Neerav Atul Patel, Mark Richard Shaw
  • Patent number: 10041679
    Abstract: A combustor for a gas turbine engine includes an inner combustor wall and an outer combustor wall radially outboard of the inner combustor wall. The inner and outer combustor walls define a combustion space therebetween with an upstream inlet and a downstream outlet. A combustor dome connects between inner and outer combustor walls at the upstream inlet of the combustion space. The combustor dome includes a plurality of circumferentially spaced apart nozzles and a plurality of tiles mounted to the combustor dome to fluidly separate a downstream side of the combustor dome from an upstream side of the combustor dome.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: August 7, 2018
    Assignee: DELAVAN INC
    Inventor: Lev A. Prociw
  • Patent number: 9989258
    Abstract: A gas turbine combustor forms a combustion region R1 therein by burning a premixed gas obtained by previously mixing a fuel and combustion air. The gas turbine combustor includes: a burner cylinder (51) in which the premixed gas passes; a film air supply port (61) that is provided on the burner cylinder 51, and supplies a film air formed into a film shape and flowing along the inner wall surface (the inner circumferential surface) of the burner cylinder (51); and a cooling passage (71) in which a cooling air passes. The cooling air cools a back-step surface (65) facing the formed combustion region R1. The cooling passage (71) includes a side from which the cooling air flows out, and the side is connected to the film air supply port (61).
    Type: Grant
    Filed: October 22, 2013
    Date of Patent: June 5, 2018
    Assignee: MITSUBISHI HITACH POWER SYSTEMS, LTD.
    Inventors: Keijiro Saito, Satoshi Takiguchi, Toshihiko Saito, Shinji Akamatsu
  • Patent number: 9982579
    Abstract: A heat shield comprising a sidewall portion, a top portion, and a plurality of flexible tabs attached to the sidewall portion is described herein, in accordance with various embodiments. The top portion may comprise an aperture. The sidewall portion may extend at an angle between 80 degrees and 100 degrees from the top portion. The sidewall portion may bound a hexagonal void. The flexible tab may comprise an angle between 80 degrees and 100 degrees. The flexible tab may be fixed to the sidewall portion, wherein the flexible tab is configured to be attached to a fitting.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: May 29, 2018
    Assignee: United Technologies Corporation
    Inventors: Pawel Socha, Richard Joseph Bulkovitch, Kelsey Honious, Jonathan C Reuben
  • Patent number: 9933161
    Abstract: A combustor dome heat shield has a heat shield panel adapted to be mounted to a combustor dome with a back face of the heat shield panel in spaced-apart facing relationship with an inner surface of the combustor dome to define an air gap between the heat shield panel and the combustor dome. Rails extend from the back face of the heat shield panel across the air gap. An anti-rotation notch is defined in at least one of the rails for receiving an anti-rotation tab of an adjacent element, such as a fuel nozzle floating collar. The rails include notch cavity rails extending on either side of the anti-rotation notch. The notch cavity rails define a notch cavity for capturing coolant air leaking through the anti-rotation notch.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: April 3, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michael Papple
  • Patent number: 9879606
    Abstract: The described method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine includes directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow, directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow being below a coking temperature of the fuel, and then feeding the cooled fuel flow from the fuel fairing to the internal fuel manifold.
    Type: Grant
    Filed: July 28, 2014
    Date of Patent: January 30, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Oleg Morenko, Bryan Olver
  • Patent number: 9829198
    Abstract: A gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss.
    Type: Grant
    Filed: August 12, 2013
    Date of Patent: November 28, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Bhawan B. Patel, Ram Kulathu, Sudhakara Reddy Annem, Balakrishna Gaja, Bharath Mandya Nagaraj
  • Patent number: 9765974
    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 exit lip has a surface treatment including a swirl-inducing relief. A gas turbine engine and a method of inducing swirl in at least one of pressurised fuel and air exiting a fuel nozzle of a gas turbine engine are also presented.
    Type: Grant
    Filed: October 3, 2014
    Date of Patent: September 19, 2017
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Yen-Wen Wang, Nigel Davenport, Eduardo Hawie
  • Patent number: 9765970
    Abstract: A combustion chamber module for an aircraft turbomachine, including an annular combustion chamber in which each of primary and dilution ports of an outer annular wall, which is located at least partly in a wake of a fuel injector, has a discharge coefficient higher than that of its homologous port of an inner annular wall. A method for designing such a module includes determining wakes generated by fuel injectors, and then geometrically defining air inlet ports of coaxial walls of the combustion chamber such that an air flow rate actually entering through ports of the outer wall is substantially equal to an air flow rate entering through ports of the inner wall.
    Type: Grant
    Filed: October 24, 2012
    Date of Patent: September 19, 2017
    Assignee: Safran Aircraft Engines
    Inventors: Sebastien Alain Christophe Bourgois, Jean-Francois Cabre
  • Patent number: 9746184
    Abstract: A combustor heat shield comprises a heat shield body adapted to be mounted to a combustor wall with a back side of the heat shield body in spaced-apart facing relationship with the combustor wall to define an air gap between the heat shield body and the combustor wall. At least one nozzle opening is defined in the heat shield bod. The opening is bordered by a nozzle opening boss. The boss extends from the back side of the heat shield body across the air gap for sealing engagement with an adjacent part of the combustor. An annular array of effusion holes is provided adjacent the nozzle opening boss. The effusion holes extend through the heat shield body for passing cooling air from the back side to a front side of the heat shield body. Fins are interspersed between the effusion holes on the back side of the heat shield.
    Type: Grant
    Filed: April 13, 2015
    Date of Patent: August 29, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Papple, Robert Sze
  • Patent number: 9726777
    Abstract: A proximity sensor includes a lead supported on an outer surface of a case structure and a sensor wire that extends from the lead and through an opening in the case structure. The sensor is formed by applying alternating layers of electrically conductive and non-conductive materials in a non-cured state. A base non-conductive layer is applied to an inner surface of the case structure around the sensor wire in a non-cured state. Once cured, a conductive layer is deposited onto the base non-conductive layer and encapsulates the sensor wire. A cover non-conductive layer is then deposited over portions of the conductive layer to insulate the conductive layer. Portions of the non-conductive layer are then removed such that an area of the conductive layer is exposed to define a sensor area.
    Type: Grant
    Filed: January 23, 2013
    Date of Patent: August 8, 2017
    Assignee: United Technologies Corporation
    Inventors: Eli Cole Warren, Jerusalem Negash
  • Patent number: 9714767
    Abstract: A premix fuel nozzle assembly includes a center body, a pilot premix fuel nozzle assembly that extends axially through the center body and that includes a premix tip having a plurality of premix tubes that each defines a premix passage and a fuel port. The premix passage of each premix tube is in fluid communication with the pilot air passage. The premix fuel nozzle assembly further includes a purge air cartridge assembly that extends axially within the pilot air passage. The purge air cartridge assembly includes a feed tube portion and a tip portion that define a purge air passage within the pilot air passage. The tip portion comprises an aft wall that extends at least partially through an opening defined by the premix tip. The aft wall includes a single axially extending orifice that is in fluid communication with the purge air passage.
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: July 25, 2017
    Assignee: General Electric Company
    Inventors: Jason Thurman Stewart, Michael Christopher Gibson, Bryan Wesley Romig
  • Patent number: 9631812
    Abstract: A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate.
    Type: Grant
    Filed: March 18, 2013
    Date of Patent: April 25, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Lucas John Stoia, Richard Martin DiCintio, William Michael Poschel, Patrick Benedict Melton