Ceramic Patents (Class 60/753)
  • Patent number: 11920789
    Abstract: A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.
    Type: Grant
    Filed: February 4, 2021
    Date of Patent: March 5, 2024
    Assignee: General Electric Company
    Inventors: Mark Willard Marusko, Michael Alan Stieg, Brian Christopher Towle
  • Patent number: 11905837
    Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.
    Type: Grant
    Filed: March 23, 2022
    Date of Patent: February 20, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Nicholas R. Overman
  • Patent number: 11867103
    Abstract: An annular resonator with a multiplicity of perforations for installation into a combustor arrangement of a static gas turbine installation, wherein the resonator is produced from refractory ceramic. A combustor arrangement for a gas turbine installation with a combustor unit, has a combustor, with a transfer line, which is arranged downstream of the combustor unit and which is designed to conduct hot gas generated by the combustor to a turbine, and with at least one resonator.
    Type: Grant
    Filed: March 16, 2020
    Date of Patent: January 9, 2024
    Assignee: Siemens Energy Global GmbH &Co. KG
    Inventor: Claus Krusch
  • Patent number: 11859819
    Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.
    Type: Grant
    Filed: October 15, 2021
    Date of Patent: January 2, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Ryan Christopher Jones, Shai Birmaher, Nicholas John Bloom, Daniel J. Kirtley, Gerardo Antonio Salazar Lois, Anquan Wang, Trevor James Hahm
  • Patent number: 11852344
    Abstract: A tubular combustion chamber system for a gas turbine unit includes a plurality of annularly arranged transition lines, which are designed to be connected at the upstream ends thereof to respective burners and to conduct hot gas produced by the burners to a turbine. The tubular combustion chamber system has a hot gas distributor, which is designed to be connected to the turbine and defines a ring channel, which is open to the turbine and into which the downstream ends of the transition lines lead. A gas turbine unit includes a plurality of annularly arranged burners, a turbine and a tubular combustion chamber system which connects the burners to the turbine.
    Type: Grant
    Filed: March 3, 2020
    Date of Patent: December 26, 2023
    Assignee: Siemens Aktiengesellschaft
    Inventors: Matthias Gralki, Claus Krusch, Daniel Schmidt
  • Patent number: 11814967
    Abstract: A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.
    Type: Grant
    Filed: June 11, 2020
    Date of Patent: November 14, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Ulysse Jacques Bernard Danteny, Laurent Cédric Zamai
  • Patent number: 11802512
    Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).
    Type: Grant
    Filed: April 13, 2021
    Date of Patent: October 31, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan-Ranjiv Joory, Benjamin Frantz Karl Villenave
  • Patent number: 11788724
    Abstract: A combustor liner has an outer liner and an inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The outer liner and the inner liner each have a converging-diverging section extending into the dilution zone of the combustion chamber and form a throat between them. A bridge member extends across the converging-diverging sections to form a damper cavity therebetween. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat, and includes a damper inlet feed member on a downstream portion of the converging-diverging section, so that an acoustic damper is defined by the converting-diverging section, the bridge, and the damper inlet feed. The acoustic damper dampens acoustic characteristics of the combustor.
    Type: Grant
    Filed: September 2, 2022
    Date of Patent: October 17, 2023
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Hiranya Nath, Ravindra Shankar Ganiger, Michael A. Benjamin
  • Patent number: 11754289
    Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.
    Type: Grant
    Filed: December 17, 2020
    Date of Patent: September 12, 2023
    Assignee: Delavan, Inc.
    Inventors: Jason Ryon, Brandon P. Williams, Lev Alexander Prociw
  • Patent number: 11525580
    Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.
    Type: Grant
    Filed: December 17, 2020
    Date of Patent: December 13, 2022
    Assignee: Delavan, Inc.
    Inventors: Jason Ryon, Brandon P. Williams, Lev Alexander Prociw
  • Patent number: 11506383
    Abstract: The gas turbine combustor liner can delimit a combustion chamber, and have at least one monolithic ceramic block having a first face exposed to the combustion chamber and a second face opposite the first face, and a 3D fabric of ceramic fibers partially embedded inside the monolithic ceramic block, and partially extending outside the second face of the monolithic ceramic block, away from the combustion chamber.
    Type: Grant
    Filed: October 9, 2020
    Date of Patent: November 22, 2022
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventor: Larry Lebel
  • Patent number: 11486309
    Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter at least partially within the combustor case, and a removable surface igniter. The torch igniter includes a combustion chamber, a cap configured to receive a fuel injector, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, an aperture, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The torch igniter is configured to receive the removable surface igniter through the aperture. An internal end of the removable surface igniter extends through the aperture into the combustion chamber of the torch igniter.
    Type: Grant
    Filed: December 17, 2020
    Date of Patent: November 1, 2022
    Assignee: Delavan Inc.
    Inventors: Jason Ryon, Lev Alexander Prociw, Brandon P. Williams
  • Patent number: 11359810
    Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component; and a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow in a lateral direction parallel to the second surface of the first component such that a cross flow is generated.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: June 14, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dennis M. Moura, Carey Clum
  • Patent number: 11280215
    Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: March 22, 2022
    Assignee: General Electric Company
    Inventors: Robert Frederick Bergholz, Jason Randolph Allen, Robert David Briggs, Kevin Robert Feldmann, Curtis Walton Stover, Zachary Daniel Webster, Fernando Reiter
  • Patent number: 11208899
    Abstract: A cooling assembly comprises a pin disposed inside a first chamber of an airfoil. The first chamber is disposed inside the tip end comprising a tip floor. The pin extends from a first end to a second end along a pin axis. The first end is coupled with a first surface of the first chamber and the second end is coupled with an inner floor surface of the tip floor such that the pin increases a structural load support level of the tip floor. A cooling conduit is placed inside the pin through which coolant flows. The cooling conduit is elongated along and extends around a conduit axis and is fluidly coupled with conduit channels disposed between the first and second ends of the pin. The conduit channels direct coolant out of the cooling conduit or direct coolant into the cooling conduit.
    Type: Grant
    Filed: March 14, 2018
    Date of Patent: December 28, 2021
    Assignee: General Electric Company
    Inventors: Thomas Earl Dyson, Nicholas William Rathay, Gustavo Ledezma
  • Patent number: 11209166
    Abstract: A combustor assembly for a gas turbine engine defining a radial direction and a circumferential direction includes a liner assembly at least partially defining a combustion chamber and including at least one liner extending between a downstream end and an upstream end, the downstream end of the at least one liner defining a radial opening and an interface surface extending along the circumferential direction and along the radial direction; and a seal member including a body, a flange, and a radial element, the body defining a body surface extending along the radial direction and positioned adjacent the interface surface of the at least one liner, the flange extending forward from the body, and the radial element coupled to the flange and extending into the radial opening defined by the at least one liner.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: December 28, 2021
    Assignee: General Electric Company
    Inventors: Ernesto Andres Vallejo Ruiz, Aaron Michael Dziech, Jonathon Eli Farmer
  • Patent number: 11047574
    Abstract: A combustor assembly for a gas turbine engine defining a radial direction and a circumferential direction includes a liner assembly at least partially defining a combustion chamber and including at least one liner formed of a ceramic matrix composite material and extending between a downstream end and an upstream end, the downstream end of the at least one liner defining an interface surface extending along the circumferential direction; and a seal member also formed of a ceramic matrix composite material and bonded to the interface surface of the at least one liner, the seal member defining a downstream surface for contacting an adjacent component to form a seal with the adjacent component.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: June 29, 2021
    Assignee: General Electric Company
    Inventors: Ernesto Andres Vallejo Ruiz, Douglas Craig Anderson
  • Patent number: 10968750
    Abstract: An apparatus and method for cooling a component for a turbine engine which generates a hot gas flow and provides a cooling fluid flow, the component comprising a body having an outer surface, at least a portion of which is exposed to the hot gas flow to define a hot surface, a cooling cavity located within the body and fluidly coupled to the cooling fluid flow and a pin located within the cooling cavity and defining a cooling hole.
    Type: Grant
    Filed: September 4, 2018
    Date of Patent: April 6, 2021
    Assignee: General Electric Company
    Inventors: Zachary Daniel Webster, Gregory Terrence Garay, Xi Yang, Tingfan Pang, Steven Robert Brassfield
  • Patent number: 10941937
    Abstract: A gasket for installation within a cavity between a support shell and a liner panel of a combustor wall assembly, the support shell having a multiple of impingement holes, and the liner panel having a multiple of film holes, the gasket including a multiple of cells arranged with respect to the multiple of impingement holes and the multiple of film holes, wherein at least one of the multiple of cells segregate a respective subset of the multiple of impingement holes and a subset of the multiple of film holes.
    Type: Grant
    Filed: March 20, 2017
    Date of Patent: March 9, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Stephen K. Kramer, Jose E. Ruberte Sanchez
  • Patent number: 10935240
    Abstract: A heat shield for use in a combustor of a gas turbine engine including a plurality of standoff pins that extend from a cold side, the plurality of standoff pins at least partially surround an attachment stud, the cold side including at least one film cooling hole adjacent to the plurality of standoff pins and the attachment stud.
    Type: Grant
    Filed: April 23, 2015
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Hoyt Y Chang, Brooks E Snyder, Thomas N Slavens
  • Patent number: 10935244
    Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
    Type: Grant
    Filed: October 23, 2018
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Stanislav Kostka, Frank J. Cunha
  • Patent number: 10830435
    Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface, a rail member disposed on the cold side proximate a first portion of the outer perimeter, the rail member having an outer wall and an inner wall, and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having a cross sectional area that increases from the inner wall to the outer wall.
    Type: Grant
    Filed: February 6, 2018
    Date of Patent: November 10, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E Sobanski, Steven D Porter
  • Patent number: 10801727
    Abstract: Systems and methods may be provided in which a combustion liner is configured to be included in an aft end of a combustor for a gas turbine engine. An aft seal may be movably engaged with the combustion liner in a seal engagement region. The combustion liner may comprise an inlet formed in an outer surface of the combustion liner to receive a cooling fluid, and an outlet in fluid communication with the inlet via a passageway formed within the combustion liner, the outlet disposed in an inner surface of the combustion liner in the seal engagement region.
    Type: Grant
    Filed: July 6, 2018
    Date of Patent: October 13, 2020
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventors: Christopher Dwayne DeBruhl, Timothy C. Roesler
  • Patent number: 10788212
    Abstract: A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.
    Type: Grant
    Filed: January 11, 2016
    Date of Patent: September 29, 2020
    Assignees: General Electric Company, ExxonMobil Upstream Research Company
    Inventors: Jonathan Kay Allen, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Bradford David Borchert, Michael V. Kazakis, Igor Petrovich Sidko
  • Patent number: 10697314
    Abstract: A turbine shroud assembly of a gas turbine engine for combustion of fuel mixed with air to produce exhaust products includes a blade track having an I-beam construction including ceramic materials and defining a flow surface to guide exhaust products through a turbine section of the gas turbine engine to expand the exhaust products across the turbine section to produce force.
    Type: Grant
    Filed: October 14, 2016
    Date of Patent: June 30, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: David J. Thomas, Jeffrey A. Walston
  • Patent number: 10684014
    Abstract: A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.
    Type: Grant
    Filed: August 4, 2016
    Date of Patent: June 16, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: San Quach, Brian T. Hazel, Kaitlin M. Tomeo, Robert Selinsky, Jr., Aaron S. Butler, John S. Tu, William F. Werkheiser, Jessica L. Serra
  • Patent number: 10619857
    Abstract: A combustor panel may include an attachment feature having a central longitudinal axis and extending from a cold side of the combustor panel. The attachment feature may include a tip portion and a base portion and the attachment feature may be configured to extend through a combustor shell such that the tip portion is disposed outward of a diffuser-facing side of the combustor shell. The base portion may be configured to be disposed between the cold side of the combustor panel and the diffuser-facing side of the combustor shell. The attachment feature may define a core passage extending from an inlet opening defined on the tip portion and extending partially through the attachment feature to terminate within the attachment feature. The attachment feature may also define an offshoot passage extending from the core passage to an outlet opening defined on the base portion.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: April 14, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jonathan Lemoine, Steven D. Porter, Kevin Zacchera
  • Patent number: 10577977
    Abstract: An assembly adapted for use in a gas turbine engine has a plurality of segments arranged to form an annular shape and seal elements arranged circumferentially between the segments. The assembly further includes retention means for restraining movement of the plurality of seal members in the radial direction away from a central axis and out of position relative to the plurality of segments.
    Type: Grant
    Filed: February 22, 2017
    Date of Patent: March 3, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Alexandra R. Baucco
  • Patent number: 10551066
    Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: February 4, 2020
    Assignee: United Technologies Corporation
    Inventors: Donald W. Peters, San Quach, Jeffrey T. Morton, Matthew D. Parekh
  • Patent number: 10519790
    Abstract: A turbine component includes an outer shroud arranged within a turbine and further including opposed extending portions. The component further provides an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and including opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The component further provides a load path forming region at least partially extending between facing surfaces of each arcuate portion and corresponding extending portion. During operation of the turbine, load path forming regions extend into direct contact between at least a portion of the facing surfaces of each arcuate portion and corresponding extending portion, resulting in formation of a loading arrangement having generally evenly distributed radial load forces at the load path forming regions.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: December 31, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Troy Hafner, John McConnell Delvaux, Glenn Curtis Taxacher
  • Patent number: 10495309
    Abstract: A component for at least one of a combustion section or a turbine section of a gas turbine engine is provided. The combustion section and turbine section of the gas turbine engine at least partially define a core air flowpath, and the component includes a wall. The wall, in turn, includes a hot side and an opposite cold side. The hot side is exposed to and at least partially defines the core air flowpath when the component is installed in the gas turbine engine. The wall is manufactured to include surface contouring on the cold side of the wall to structurally accommodate a thermal management feature of the wall.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: December 3, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 10480321
    Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
    Type: Grant
    Filed: November 18, 2015
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Patrick E. Bailey, Samuel J. Lacombe, Eric W. Engebretsen, Rodney D. Conrad, Matthew J. Kappes
  • Patent number: 10386067
    Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.
    Type: Grant
    Filed: September 15, 2016
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Scott A. Elliott, Robert M. Sonntag, John S. Tu, Anthony Van, Joseph J. Sedor, Robert Selinsky, Jr., John J. Rup, Jr., Neil B. Ridgeway, Gerard V. Cadieux, Jeffrey Leon, Monica Pacheco-Tougas, Lisa A. Jenkins, Lisa Tse, Andrew Cervoni, Frank J. Trzcinski
  • Patent number: 10378771
    Abstract: A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner attached to or formed integrally with the combustor dome. The combustion chamber liner extends between a forward end and an aft end, and together with the combustor dome at least partially defines a combustion chamber. The combustor assembly additionally includes a mounting assembly attached to the liner proximate the forward end of the liner for supporting the combustor dome and combustion chamber liner within the gas turbine engine relative to a structural component of the gas turbine engine.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
  • Patent number: 10208955
    Abstract: A combustor is provided. The combustor may comprise a shell including a ceramic material. A gradient transition from ceramic to metal may have a predominantly ceramic side coupled to the shell. A metal mating surface may also be coupled to a predominantly metal side of the gradient transition from ceramic to metal.
    Type: Grant
    Filed: April 7, 2015
    Date of Patent: February 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Hoyt Y. Chang
  • Patent number: 10190773
    Abstract: A combustor floatwall panel includes a stack of layers of a sintered material forming in the aggregate a panel, an attachment stud, and a cooling flow passageway. The panel has a first surface and a second surface parallel to the first surface. The attachment stud projects from the second surface. The cooling flow passageway includes a feeder hole extending through the attachment stud, and at least one effusion cooling hole extending to the first surface. The effusion cooling hole is fluidly connected to the feeder hole. The effusion cooling hole extends along a first axis where the effusion cooling hole meets the first surface. The feeder hole extends along a second axis. The first axis is at a first angle relative to the first surface. The second axis is at a second angle relative to the first surface. The second angle is greater than the first angle.
    Type: Grant
    Filed: October 23, 2014
    Date of Patent: January 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Russell B. Hanson, George F. Titterton, III
  • Patent number: 10168051
    Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. A mounting assembly attaches the forward end of the liner to the annular dome. The mounting assembly includes a pin extending through the slot and the forward end of the annular dome. The mounting assembly also includes a grommet positioned in an opening in the forward end of the liner. The grommet is also positioned around the pin to protect the liner during operation of the gas turbine engine.
    Type: Grant
    Filed: September 2, 2015
    Date of Patent: January 1, 2019
    Assignee: General Electric Company
    Inventors: Nicholas John Bloom, Michael Alan Stieg, Brian Christopher Towle
  • Patent number: 10072572
    Abstract: A gas turbine engine. The engine includes a first compressor coupled to a first turbine by a first shaft, the first turbine having first and second turbine stages. A first combustor is provided downstream of the first compressor and upstream of the first stage of the first turbine. A second combustor is provided downstream of the first stage of the first turbine, and upstream of the second stage of the first turbine. A further turbine is provided downstream of the first turbine, and is coupled to a further compressor by a further shaft.
    Type: Grant
    Filed: March 16, 2015
    Date of Patent: September 11, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Ahmad Razak
  • Patent number: 10060626
    Abstract: A gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.
    Type: Grant
    Filed: December 13, 2016
    Date of Patent: August 28, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Kay Heinze, Stefan Penz, Ivo Szarvasy
  • Patent number: 10041677
    Abstract: A combustion liner for use in a combustor assembly is provided. The combustion liner includes a side wall that defines a combustion chamber having a main flow axis extending therethrough. The combustion chamber channels a flow of combustion gas therethrough along a mixer swirl flow axis oriented obliquely relative to the main flow axis. The combustion liner also includes film cooling holes defined within the side wall. The film cooling holes are configured to discharge a pressurized fluid jet into the combustion chamber, and arranged in at least a first row and a second row positioned a first distance from the first row. The film cooling holes are arranged such that, when mixed with the flow of combustion gas, the pressurized fluid jet discharged from film cooling holes in the first row is directed along a discharge flow axis misaligned from film cooling holes in the second row.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: August 7, 2018
    Assignee: General Electric Company
    Inventors: Erich Robert Fitzpatrick, Michael Alan Stieg, Kimberly Lynne Christman Kenoyer
  • Patent number: 9976434
    Abstract: A brush seal assembly may include a packing body that includes an insertion groove formed inward in a circumferential direction. The insertion groove may be positioned between a rotating body and a fixed body. The packing body may include insertion holes having openings disposed toward the insertion groove at different positions and in different directions. A brush seal part includes a brush and a support member that supports the brush. The brush may extend toward the rotating body when brush is disposed in the insertion groove. A thermal expansion member may adhere to a side of the support member and thermally expand in a circumferential direction of the packing body. Fixing members may be inserted into the insertion holes, respectively, from an outside of the packing body to maintain a fixed state of the brush seal part in radial and circumferential directions of the packing body.
    Type: Grant
    Filed: June 8, 2015
    Date of Patent: May 22, 2018
    Assignee: DOOSAN Heavy Industries Construction CO., LTD.
    Inventor: Mahmut Faruk Aksit
  • Patent number: 9939158
    Abstract: A combustor includes a first tube which supplies fuel and air from an opening formed in a distal end thereof, and a second tube which is configured such that flames are formed on an inner circumferential side thereof by the fuel and the air and the distal end of the first tube is inserted into an inner circumferential side of a proximal end thereof. The first tube includes a first tube main body and a ring part forming the distal end of the first tube. The ring part has a main body of a tubular shape and a plurality of protrusions that are integrally formed with the main body on an outer circumferential surface of the main body and protrude radially outward. When viewed in an axial direction, the outer circumferential surface of the main body has a polygonal cross-sectional shape within a range within which the protrusions are formed.
    Type: Grant
    Filed: February 18, 2014
    Date of Patent: April 10, 2018
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Kenta Taniguchi, Norihiko Motoyama, Yoshiro Nakamura
  • Patent number: 9822979
    Abstract: A gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.
    Type: Grant
    Filed: December 13, 2016
    Date of Patent: November 21, 2017
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Kay Heinze, Stefan Penz, Ivo Szarvasy
  • Patent number: 9784215
    Abstract: A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion.
    Type: Grant
    Filed: November 7, 2014
    Date of Patent: October 10, 2017
    Assignee: ROHR, INC.
    Inventors: Jacques Jinqiu Lu, Chad Franks, Richard S. Alloway
  • Patent number: 9732701
    Abstract: A center body attachment system may comprise an engine flange, a center body mounting assembly, and a center body. The center body mounting assembly may retain the center body and the engine flange in slidable engagement, whereby the engine flange and the center body may expand and contract at different rates. The center body may comprise a housing. The housing may comprise a floating counter bore, a spring supporting the floating counter bore, and a slider radially inward of the floating counter bore and retained within the housing by a nut.
    Type: Grant
    Filed: May 12, 2014
    Date of Patent: August 15, 2017
    Assignee: ROHR, INC.
    Inventor: Jinqiu Jacques Lu
  • Patent number: 9650904
    Abstract: A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straight path segment (26) for receiving a gas flow from a respective combustor. A straight ceramic liner (40) may be inwardly disposed onto a metal outer shell (38) along the straight path segment of the exit piece. Structural arrangements are provided to securely attach the ceramic liner in the presence of substantial flow path pressurization. Cost-effective serviceability of the transition duct systems is realizable since the liner can be readily removed and replaced as needed.
    Type: Grant
    Filed: January 21, 2016
    Date of Patent: May 16, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventor: David J. Wiebe
  • Patent number: 9644843
    Abstract: A combustor heat shield for a gas turbine engine has a heat shield panel adapted to be mounted to an inner surface of a combustor shell with a back face of the panel spaced-apart from the combustor shell to define an air gap therewith. Studs project from the back face of the panel for engagement in corresponding mounting holes defined in the combustor shell. Each stud has a threaded distal end portion for engagement with a nut outside of the combustor shell. At least one of the studs has a channel defined in a peripheral surface thereof. The channel extends longitudinally along the stud from an inlet end connectable to a source of cooling air outside of the combustor shell to an outlet end disposed within the air gap for locally providing cooling air at the base of the stud.
    Type: Grant
    Filed: October 8, 2013
    Date of Patent: May 9, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Jason Herborth
  • Patent number: 9618207
    Abstract: A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straight path segment (26) and an arcuate connecting segment (36). A respective straight metal liner (92) and an arcuate metal liner (94) may be each inwardly disposed onto a metal outer shell (38) along the straight path segment and the arcuate connecting segment (36) of the exit piece. Structural arrangements are provided to securely attach the respective liners in the presence of substantial flow path pressurization. Cost-effective serviceability of the transition duct systems is realizable since the liners can be readily removed and replaced as needed.
    Type: Grant
    Filed: January 21, 2016
    Date of Patent: April 11, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventor: David J. Wiebe
  • Patent number: 9568036
    Abstract: A push-lock pin for connecting a tile to a gas turbine engine wall according to an exemplary aspect of the present disclosure includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including a push-down pop-up mechanism and a locking mechanism, the locking mechanism moveable to a locked position such that the locking mechanism limits movement of a tile away from a gas turbine engine wall; and a stop feature to limit movement of the tile toward the gas turbine engine wall.
    Type: Grant
    Filed: February 6, 2014
    Date of Patent: February 14, 2017
    Assignee: United Technologies Corporation
    Inventors: Jose E. Ruberte Sanchez, Timothy J. McAlice
  • Patent number: 9551491
    Abstract: The invention relates a method for mixing a dilution air with a hot main flow in a sequential combustion system of a gas turbine, wherein the gas turbine essentially comprises at least one compressor, a first combustor which is connected downstream to the compressor, and a second combustor. The hot gases of the first combustor are admitted to at least one intermediate turbine or directly or indirectly to at least one second combustor, wherein the hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery device. The method comprises a coaxial injection of first combustor liner cooling air with second combustor liner cooling air, the first combustor liner cooling air having a sufficient excess pressure margin with respect to the second combustor liner cooling air.
    Type: Grant
    Filed: August 23, 2013
    Date of Patent: January 24, 2017
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Adnan Eroglu, Ewald Freitag