In An Axial Direction Patents (Class 60/757)
  • Patent number: 11022068
    Abstract: A monolithic heater body may include a combustor body, a hot-side heat exchanger body, and an eductor body. The combustor body may define a combustion chamber and a conditioning conduit circumferentially surrounding the combustion chamber. The conditioning conduit may fluidly communicate with the combustion chamber at a distal portion of the combustion chamber. The hot-side heat exchanger body may define a hot-side heat exchanger that includes a heating fluid pathway fluidly communicating with a proximal portion of the combustion chamber. The eductor body may define an eduction pathway fluidly communicating with a downstream portion of the heating fluid pathway and a proximal portion of the conditioning conduit.
    Type: Grant
    Filed: May 20, 2020
    Date of Patent: June 1, 2021
    Assignee: General Electric Company
    Inventors: Joshua Tyler Mook, Kevin Michael VandeVoorde, Aigbedion Akwara, Michael Robert Notarnicola, Jason Joseph Bellardi, Mohammed El Hacin Sennoun, Mohamed Osama, Zachary William Nagel
  • Patent number: 11022313
    Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.
    Type: Grant
    Filed: June 22, 2016
    Date of Patent: June 1, 2021
    Assignee: General Electric Company
    Inventors: Gregory Allen Boardman, Pradeep Naik, Allen Michael Danis
  • Patent number: 11022308
    Abstract: A combustor for a turbine engine includes a first liner and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner is a first double wall liner with a first wall forming a portion of the combustion chamber and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The combustor further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall, through the first wall, and into the combustion chamber.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: June 1, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Nagaraja S. Rudrapatna, Ian Critchley, Jeffrey Spencer, Philip Smalley
  • Patent number: 11022307
    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, a rail member disposed on the cold side proximate an 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 an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.
    Type: Grant
    Filed: February 22, 2018
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technology Corporation
    Inventors: Jon E Sobanski, Steven D Porter
  • Patent number: 10995635
    Abstract: A gas turbine engine component assembly is provided. The gas turbine engine comprises: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate mitigation device extending from the first surface of the second component a selected distance wherein the particulate mitigation device has an opening therethrough in fluid connection with the cooling channel, and wherein the selected distance is selected to reduce the amount of particulate entering the cooling channel.
    Type: Grant
    Filed: November 30, 2017
    Date of Patent: May 4, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Scott H. Lamson
  • Patent number: 10995956
    Abstract: A combustor (3) includes: a fuel nozzle configured to inject fuel; a tubular body (24) having a tubular shape in which a combustion region through which combustion gas flows is formed inside, and in which a plurality of slits (50) are formed extending in the circumferential direction at intervals in the circumferential direction; and throttle pieces (60) which are fitted into the slits (50), project radially inward from the inner circumferential side of the tubular body (24), and have a throttle face that extends along the flow direction of the combustion gas as it extends from the radially outer side inward.
    Type: Grant
    Filed: March 28, 2017
    Date of Patent: May 4, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Shuhei Kajimura, Kenji Miyamoto, Taiki Kinoshita, Kotaro Miyauchi
  • Patent number: 10961910
    Abstract: In a combustion cylinder, an outer-side region of a cooling part on an outer side with regard to a reference line orthogonal to a radial direction and an axial direction of a gas turbine and passing through a center of a combustor basket, and an inner-side region of the cooling part on an inner side with regard to the reference line are set. A connection angle at an intersection between an extension line of an outer surface of the combustor basket along the axial direction and an inner surface of a combustor transition piece is set. First regions are set at positions near the reference line, and second regions, with a larger connection angle than the first regions, are set at positions farther from the reference line than the first regions. The second regions are set to have a higher flow rate of a cooling medium than the first regions.
    Type: Grant
    Filed: October 28, 2016
    Date of Patent: March 30, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kenji Sato, Kentaro Tokuyama
  • Patent number: 10941943
    Abstract: An assembly for a turbomachine combustion chamber, including a boss for turbomachine combustion chamber, including a tubular body configured to be inserted in a receiving orifice formed in an annular wall of a flame tube and to accommodate a shank of a connecting pin for connecting the flame tube to an external casing, a first end of the boss including an annular flange configured to prevent radial translational movement of the boss in a first direction, and a second end of the boss being configured to be crimped to the wall of the flame tube so as to prevent radial translational movement of the boss in a second direction, and an annular element configured to fit coaxially with the receiving orifice and in radial contact with the annular wall of the flame tube on the one hand and with the annular flange of the boss on the other.
    Type: Grant
    Filed: June 19, 2015
    Date of Patent: March 9, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Ludovic Andre Joel Naudot, Philippe Olharan, Jean Menet-Haure
  • Patent number: 10837646
    Abstract: A combustion chamber shingle arrangement of a gas turbine, including a combustion chamber shingle, at least one threaded bolt configured for attaching the combustion chamber shingle, and a base body connecting the threaded bolt to the combustion chamber shingle, wherein the base body comprises a platform and a connection area that connects the platform to the combustion chamber shingle, wherein the threaded bolt is arranged at the platform, and wherein a hollow space is embodied between the platform and the combustion chamber shingle.
    Type: Grant
    Filed: February 26, 2018
    Date of Patent: November 17, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Michael Ebel, Kay Heinze, Stefan Penz
  • Patent number: 10823414
    Abstract: A gas turbine engine component assembly including: a first component having a first surface and second surface opposite the first surface, the first component includes a cooling hole extending from second surface to first surface; a second component having a first surface and second surface, the first surface of first component and second surface of second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling second surface of second component; and an aperture extension feature in the second component and extending into cooling channel, the aperture extension feature includes a passageway fluidly connecting cooling channel to an area located proximate to the first surface of second component, the aperture extension feature includes a face and inlet located in the first face to fluidly connect passageway to cooling channel, the first face being oriented between 0° and 120° relative to second surface of second component.
    Type: Grant
    Filed: March 19, 2018
    Date of Patent: November 3, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Scott H. Lamson
  • Patent number: 10815789
    Abstract: An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.
    Type: Grant
    Filed: February 13, 2016
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Jason Randolph Allen
  • Patent number: 10808930
    Abstract: A combustor shell is provided. The combustor shell may include a first aperture at least partially defined by an inner wall of the combustor shell and passing from a diffuser-facing side of the combustor shell to a combustor-facing side of the combustor shell. The combustor shell may include a spacer comprising a first segment coupled to a first flange, wherein the first flange is disposed on the diffuser-facing side of the combustor shell, wherein an outer wall of the spacer is coupled with at least a portion of an inner wall of the combustor shell.
    Type: Grant
    Filed: June 28, 2018
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Kevin W. Schlichting
  • Patent number: 10794595
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Randal G. McKinney, Frank J. Cunha, Stanislav Kostka, Jr.
  • Patent number: 10782024
    Abstract: A combustion duct assembly for a gas turbine includes a liner, an annular spring seal and a transition piece. The annular spring seal is outwardly convex and coupled to an outer face of the downstream side of the liner. The transition piece has includes an inner wall and an outer wall that surrounds the inner wall. The convex part of annular spring seal is operable to elastically engage the inner wall of the transition piece. An end portion of the downstream side of the annular spring seal is fixed to the line. The annular spring seal includes a plurality of through holes formed in an upstream side of a point where the annular spring seal comes into contact with the inner wall. The liner includes a plurality of vent holes formed in an inner area surrounded by the spring seal.
    Type: Grant
    Filed: June 10, 2016
    Date of Patent: September 22, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Heon Seop Jin
  • Patent number: 10767490
    Abstract: Components for gas turbine engines and methods of making the same, the components including a component body having an external side wall and an internal side wall and defining at least a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall, at least one segmented rib extending within the component body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities, the at least one segmented rib comprising at least two rib segments separated by a segment gap, and a discharge hole formed in the external side wall fluidly connected the segment gap to an exterior surface of the component body.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: September 8, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10670270
    Abstract: A gas turbine combustion chamber with an inner combustion chamber wall and an outer combustion chamber wall, which form an annular combustor, is provided. Mixing air holes are formed in the inner combustion chamber wall and the outer combustion chamber wall in a circumferentially distributed manner. The respective combustion chamber wall is bulged in the area of the mixing air holes towards the interior space of the combustion chamber wall and the mixing air hole is arranged inside the bulge. The mixing air hole is formed at an inflow surface of the bulge with respect to the through-flow direction of the combustion chamber.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten Clemen
  • Patent number: 10655856
    Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: May 19, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jonathan J. Eastwood, Dennis M. Moura, Lee E. Bouldin, Monica Pacheco-Tougas
  • Patent number: 10648667
    Abstract: A combustion chamber includes a duct wall for guiding a hot gas flow in a hot gas flow path during operation. The duct wall is a double-walled construction including an inner face, an outer face, and a wall cavity. A sleeve at least partly encloses the duct wall for guiding a cooling gas in a cooling channel between the sleeve and the duct wall along the outer surface of the duct wall to an exit end, and the cavity opens to the cooling channel. A gas turbine is disclosing as having such a combustion chamber.
    Type: Grant
    Filed: March 11, 2016
    Date of Patent: May 12, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Michael Thomas Maurer, Felix Baumgartner
  • Patent number: 10641492
    Abstract: A combustor including a transition piece that defines a flow channel therein; a combustor basket inserted in the transition piece from an upstream side of the flow channel that sends a combustion gas through the flow channel and defines a gap through which a compressed air is sent with an inner peripheral surface of the transition piece; wherein the combustor basket includes a notch portion recessed from an end of the combustor basket on a downstream side toward the upstream side, and a purge air introduction hole through which the compressed air in the gap is introduced into the notch portion.
    Type: Grant
    Filed: September 18, 2015
    Date of Patent: May 5, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Naoki Tsunoda, Satoshi Takiguchi, Shinji Akamatsu, Koichi Nishida, Katsunori Tanaka
  • Patent number: 10619488
    Abstract: An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: April 14, 2020
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Jonathan Michael Rausch, Emily Rosette Clark
  • Patent number: 10605170
    Abstract: An engine component for a gas turbine engine which generates a hot combustion gas flow adjacent a hot surface and provides a cooling fluid flow adjacent a cooling surface comprises a wall separating the hot combustion gas flow and the cooling fluid flow. At least one concavity is provided in the cooling surface and at least one film hole is provided in the cooling surface providing the cooling fluid flow to the hot surface. An inlet for the film hole is spaced from the at least one concavity, located upstream of the at least one concavity and in alignment with the at least one concavity relative to the cooling fluid flow.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: March 31, 2020
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 10533745
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: January 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Stanislav Kostka, Jr.
  • Patent number: 10533746
    Abstract: A gas turbine engine combustion chamber arrangement includes an annular outer wall and annular inner wall including an upstream and a downstream row of tiles. The downstream end of each tile in the upstream row of tiles has a rail extending towards and sealing with the outer wall and a lip extending in a downstream direction towards the tiles in the downstream row of tiles. The outer wall has a row of apertures to direct coolant onto the lips of the tiles in the upstream row of tiles. The downstream end of each tile in the upstream row of tiles has a plurality of fences extending in a downstream direction from the rail and each fence extends from the outer surface of the lip towards the outer wall. The row of apertures in the annular outer wall is arranged to direct coolant onto the lip between two circumferentially adjacent fences.
    Type: Grant
    Filed: November 22, 2016
    Date of Patent: January 14, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: John E Rimmer, Michael A Macquisten, Stephen J Mills, Jochen Rupp, Lynn I Steward, Murthy V Ravikanti
  • Patent number: 10494939
    Abstract: An engine component assembly includes at least one cavity that is in communication with a source of cooling air. An insert disposed within the cavity includes a plurality of scoops protruding into a flow of cooling air for directing cooling air through the insert and against an inner surface of the cavity.
    Type: Grant
    Filed: January 28, 2015
    Date of Patent: December 3, 2019
    Assignee: United Technologies Corporation
    Inventors: Brandon W. Spangler, Atul Kohli
  • Patent number: 10443846
    Abstract: A method of fabricating a combustor thermal shield comprising a combustor panel, a cooling feature, and an attachment feature, the combustor thermal shield to be used in a gas turbine engine combustor, includes shaping a sheet of material used to form the combustor panel. The method also includes additively manufacturing the cooling feature onto the sheet of material forming the combustor panel. The method also includes attaching the attachment feature to the sheet of material forming the combustor panel. The method also includes curving the sheet of material forming the combustor panel to achieve a curve profile according to a design of the gas turbine engine combustor.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Edward R. Bareiss
  • Patent number: 10436039
    Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.
    Type: Grant
    Filed: October 10, 2014
    Date of Patent: October 8, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brooks E. Snyder, Thomas N. Slavens
  • Patent number: 10415477
    Abstract: A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner surface facing away from the outer shell and an outer surface facing toward the outer shell, and the outer surface has one or more false flanges. At least one of the one or more false flanges includes a first surface protruding from the outer surface and facing the outer shell, and a flow diverting portion extending between the first surface and the outer surface of the inner shell. The flow diverting portion includes a first portion that diverges in a first circumferential direction between the first surface and the outer surface.
    Type: Grant
    Filed: July 31, 2013
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Brian David Moran, Kyle Eric Benson, Jeffery Craig Moree, Chandresh R. Shah, Xiaoqiang Zeng
  • Patent number: 10408452
    Abstract: In an embodiment of the invention, a dual-wall casing for a combustor comprises an outer wall and an inner wall defining a channel therebetween. The walls are fastened together by a bolt which extends from the inner wall and across the channel. In use, the inner wall is exposed to combustion products. Cooling is provided by a primary inlet hole extending through the outer wall and arranged upstream (with respect to the direction of flow of coolant in the channel) of the bolt and an array of effusion holes extending through the inner wall and positioned with their inlet in line of sight of the primary inlet hole. The primary inlet hole is sized with respect to the array of effusion holes such that it has a flow area which causes locally negligible flow restriction.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: September 10, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: John E. T. Rimmer, Nicholas M Brown
  • Patent number: 10408453
    Abstract: A grommet may define a dilution hole in a combustor panel. The grommet may comprise a set of upstream features such as, for example, a first inlet leading into a first plurality of passages with the first plurality of passages each having a first outlet directed towards an inner diameter of the grommet. A set of perimeter features may include a second inlet leading into a convective cooling passage having a plurality of internal cooling features. The convective cooling passage may further lead into a second plurality of passages each having a second outlet extending about the inner diameter of the grommet in a circumferential direction A set of downstream features may include a third inlet leading to a third plurality of passages each having a third outlet directed towards an outer diameter of the grommet.
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: September 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dominic Mongillo, Christopher Whitfield, Tracy Propheter-Hinckley
  • Patent number: 10344979
    Abstract: A heat resistant panel has a bulkhead and a swirler adjacent a combustion chamber. The heat resistant panel comprises an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead. A second exit port at a downstream end thereof is configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends. The first and second directions have opposed axial components. A heat resistant structure and a combustor are also disclosed.
    Type: Grant
    Filed: January 9, 2015
    Date of Patent: July 9, 2019
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Timothy S. Snyder
  • Patent number: 10301964
    Abstract: One exemplary embodiment of this disclosure relates to a component for a gas turbine engine. The component includes a baffle provided in an internal cavity of the component. The baffle includes a wall having an orifice therethrough, and the baffle further includes a lobe extending from the wall and at least partially covering the orifice.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: May 28, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Atul Kohli
  • Patent number: 10281152
    Abstract: A thermal mechanical dimple array for combustor liners of gas turbine engines are located at known hot spots along liner to reduce stress and minimize cracking. Such arrays have indentations in the liners at the hot spots that act to thermal mechanically flex the liner at the hot spot away from the heat source and distribute stresses such that cracking of the liner is reduced and durability is improved.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: May 7, 2019
    Assignee: United Technologies Corporation
    Inventor: Hoyt Y. Chang
  • Patent number: 10222064
    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: September 30, 2014
    Date of Patent: March 5, 2019
    Assignee: United Technologies Corporation
    Inventors: Stanislav Kostka, Frank J. Cunha
  • Patent number: 10215417
    Abstract: The invention refers to a sequential combustor arrangement having a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer includes of injection tubes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber. A flow guide is arranged in the connecting duct and/or the injection tubes for guiding the dilution gas into the injection tubes. The invention further refers to a gas turbine and a method for operating a gas turbine with such a sequential combustor arrangement.
    Type: Grant
    Filed: July 9, 2015
    Date of Patent: February 26, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Xianfeng Gao, Luis Tay Wo Chong Hilares
  • Patent number: 10215411
    Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: February 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: John S. Tu, James B. Hoke, David Kwoka, Jonathan Jeffery Eastwood
  • Patent number: 10197285
    Abstract: A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: February 5, 2019
    Assignee: United Technologies Corporation
    Inventors: James P. Bangerter, Thomas R. Russo, Russell B. Hanson, Kevin J. Low
  • Patent number: 10184662
    Abstract: A gas turbine combustor achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. The structure of the gas turbine combustor includes a plurality of circularity recesses formed on a side of an annular passage on a partial area of a combustion liner that requires cooling. Each of the circularity recesses has a rectangular surface forming a convex at a right angle with respect to a flowing direction of combustion air. The circularity recesses form a rectangular triangle having an oblique surface facing upstream of the flowing direction of the combustion air.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: January 22, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Osami Yokota, Masataka Hidaka, Shohei Numata, Tetsuma Tatsumi
  • Patent number: 10174947
    Abstract: The present invention relates to a combustion chamber tile of a gas turbine, where the combustion chamber tile has a plurality of effusion cooling holes and a mixing air hole provided as a flow-guiding element (chute) and projecting over the surface of the combustion chamber tile, characterized in that on the side of the mixing air hole facing away from a flow along the combustion chamber tile at least one supporting element is arranged on the combustion chamber tile and on the mixing air hole. It also relates to a method for its manufacture.
    Type: Grant
    Filed: November 5, 2013
    Date of Patent: January 8, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Patent number: 10125723
    Abstract: A method includes providing an exhaust liner as a first duct, providing a second duct having an opening therein, and spacing the first duct radially inward of the second duct. A spring connects the first and second ducts together and has first and second ends. A first mount comprises a first bracket portion associated with the spring and a second bracket portion directly fixed to the first duct. The first bracket portion is directly fixed to the first end of the spring and the second end of the spring is fixed to a second mount that comprises a casing plate having an area greater than the opening. The first end of the spring and the first bracket portion are inserted through the opening and the first bracket portion is attached to the second bracket portion. The casing plate is directly fixed to a radially outward facing surface of the second duct.
    Type: Grant
    Filed: July 16, 2018
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventors: Paul R. Senofonte, Timothy J. McAlice
  • Patent number: 10113506
    Abstract: The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.
    Type: Grant
    Filed: October 13, 2015
    Date of Patent: October 30, 2018
    Assignee: AIRCELLE
    Inventors: Hélène Malot, Jean-Pierre Guegou, Philippe Bienvenu, Philippe Prunin
  • Patent number: 10101029
    Abstract: The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.
    Type: Grant
    Filed: March 30, 2015
    Date of Patent: October 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Dominic J. Mongillo, Mark F. Zelesky, Joel H. Wagner, William A. Sowa
  • Patent number: 10101030
    Abstract: A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.
    Type: Grant
    Filed: September 2, 2014
    Date of Patent: October 16, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Eric Blumer
  • Patent number: 9970355
    Abstract: The present disclosure refers to an impingement cooling arrangement for cooling a duct wall of a duct guiding a hot gas flow. The impingement cooling arrangement includes an impingement sleeve which is at least partly disposed in a compressed air plenum, and spaced at a distance to the duct wall to form a cooling flow path between the duct wall and the impingement sleeve such that cooling air injected from the compressed air plenum through apertures in the sleeve impinges on the duct wall. At least one flow diverter is arranged in the cooling flow path to divert the cross flow away from at least one aperture. Besides the impingement cooling arrangement a gas turbine with such an arrangement as well as a method for cooling a duct wall are provided.
    Type: Grant
    Filed: October 15, 2014
    Date of Patent: May 15, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Michael Thomas Maurer, Michael Huber, Selma Zahirovic
  • Patent number: 9958160
    Abstract: A component within a gas turbine engine includes a surface with one or more upstream-directed cooling film holes therethrough.
    Type: Grant
    Filed: February 4, 2014
    Date of Patent: May 1, 2018
    Assignee: United Technologies Corporation
    Inventor: James A. Dierberger
  • Patent number: 9945561
    Abstract: A gas turbine combustor part of a gas turbine includes a wall, containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction. The near wall cooling channels are each provided at one end with an inlet for the supply of cooling air, and on the other end with an outlet for the discharge of cooling air. The inlets open into a common feeding channel for cooling air supply, and the outlets open into a common discharge channel for cooling air discharge. The feeding channel and the discharge channel extend in the second direction.
    Type: Grant
    Filed: November 27, 2013
    Date of Patent: April 17, 2018
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Adnan Eroglu, Michael Thomas Maurer, Diane Lauffer
  • Patent number: 9890955
    Abstract: The invention refers to a sequential combustor arrangement comprising a first burner, a first combustion chamber, a mixer for admixing a dilution gas via a dilution gas inlet to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The sequential combustor arrangement further includes four cooling zones with a cooling channel. During operation a cooling gas flows through the cooling channels. The disclosure further refers to a method for operating a gas turbine with such a sequential combustor arrangement.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: February 13, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Ewald Freitag, Adnan Eroglu, Michael Maurer, Peter Stuttaford
  • Patent number: 9810431
    Abstract: A silo combustion chamber for a gas turbine having a flame tube having an inner wall and flame tube base delimiting a combustion chamber; an outer wall surrounding the inner wall, forming a cavity; an annular chamber at least partly surrounding the outer wall and a number of supply lines fluidically coupled to the hot side of a heat exchanger during operation of the turbine; a number of burners, each of which opens into the combustion chamber on the outlet side through an opening in the flame tube base. The oxygen supply is fluidically connected to the annular chamber. A collecting chamber is arranged over the flame tube base. The annular chamber is connected to the collecting chamber via each connecting piece, each burner is fluidically connected to the collecting chamber to supply oxygen. The cavity between the inner and outer wall is locally fluidically separated from the collecting chamber.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: November 7, 2017
    Assignee: Siemens Aktiengesellschaft
    Inventor: Martin Wilke
  • Patent number: 9651258
    Abstract: A combustor for use in a gas turbine engine includes a liner with a plurality of tiles coupled to a shell via a plurality of fasteners. Each of the plurality of fasteners extends through at least one of the tiles.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: May 16, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Charles B. Graves, William G. Cummings, III, Russell N. Bennett, Jun Shi
  • Patent number: 9625153
    Abstract: A low calorific value fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the liner also defining inner primary and intermediate regions of a combustion zone and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A nozzle assembly disposed at the closed housing end includes an air blast nozzle and surrounding swirl vanes. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner impingement cools the portion of the liner defining the combustion zone. A portion of the combustor air is introduced directly into the intermediate region.
    Type: Grant
    Filed: August 21, 2014
    Date of Patent: April 18, 2017
    Assignee: OPRA TECHNOLOGIES B.V.
    Inventors: Martin Beran, Axel Lars-Uno Eugen Axelsson
  • Patent number: 9534783
    Abstract: A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert at least partially between opposed surfaces of the support shell and the heat shield panel, the insert exposed to a combustion chamber, and the insert being flush with a hot side of the heat shield.
    Type: Grant
    Filed: July 21, 2011
    Date of Patent: January 3, 2017
    Assignee: United Technologies Corporation
    Inventors: James A. Dierberger, Masamichi Hongoh, Dennis J. Sullivan