Between Blade Edge And Static Part Patents (Class 415/173.1)
  • Patent number: 11015473
    Abstract: A blade outer air seal assembly includes a seal segment that has a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall is axially spaced from a second wall. The first and second walls extend from the base portion to an outer wall to define a circumferentially extending seal passage. A carrier has a platform. A portion of the platform is within the seal passage. A radially extending first hook protrudes from the platform and is configured to engage with a support structure.
    Type: Grant
    Filed: March 18, 2019
    Date of Patent: May 25, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William M. Barker, Thomas E. Clark, Craig R. McGarrah, Daniel J. Whitney
  • Patent number: 11015466
    Abstract: A turbine vane and a gas turbine including the same are disclosed. The turbine vane includes an air foil including a leading edge and a trailing edge, and inner and outer shrouds disposed at opposite ends of the air foil. Each of the inner and outer shrouds includes a cooling chamber, which may be formed in at least one of opposite ends of the shroud arranged in a first direction.
    Type: Grant
    Filed: December 11, 2017
    Date of Patent: May 25, 2021
    Inventors: Seongyong Jeong, Sungchul Jung
  • Patent number: 11002147
    Abstract: A gas turbine engine includes a case, a stator vane, and a retainer. The case has a first surface, a second surface, a third surface extending between the first surface and the second surface, and a hook extending from the second surface and disposed opposite the third surface. The stator vane includes a shroud body and a first flange. The retainer is arranged to seat the first flange within a first slot defined between the hook and the second surface and secure the shroud body to the case.
    Type: Grant
    Filed: August 28, 2018
    Date of Patent: May 11, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: David M. Dyer
  • Patent number: 10995627
    Abstract: A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.
    Type: Grant
    Filed: August 7, 2019
    Date of Patent: May 4, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Edward C Rice, Daniel K Vetters
  • Patent number: 10989060
    Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
    Type: Grant
    Filed: April 10, 2020
    Date of Patent: April 27, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
  • Patent number: 10969103
    Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a plate, a frame attached to the plate, and a panel. The panel is supported by the frame.
    Type: Grant
    Filed: August 11, 2014
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Hoyt Y. Chang, Michael G. McCaffrey
  • Patent number: 10961854
    Abstract: A component for use in a gas turbine engine includes a channel configured to port a gas from an inlet along a flow path. The component further includes a wall defining an outlet configured to receive the gas, the wall forming an angle with the flow path that is between 60 degrees and 120 degrees, the outlet having a first portion with a first diameter and a second portion with a second diameter, the first portion configured to receive the gas before the second portion, and the first diameter being greater than the second diameter.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: March 30, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy J. Jennings, Mark F. Zelesky
  • Patent number: 10954810
    Abstract: A unitary rub strip comprises a casing having an inner surface and an outer surface opposite the inner surface; a unitary rub strip is formed integral with the casing proximate the inner surface, wherein the unitary rub strip comprises a modified structure within the casing configured to abrade responsive to an interaction with a rotating element.
    Type: Grant
    Filed: December 17, 2018
    Date of Patent: March 23, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Lawrence Binek, Matthew B. Kennedy, Evan Butcher, Jesse R. Boyer, Vijay Narayan Jagdale, Dmytro Mykolayovych Voytovych
  • Patent number: 10927695
    Abstract: A blade outer air seal includes a seal body that has a channel on a radially inner side that defines a first height portion outside of the channel and a second height portion within the channel. A first cavity is in the first height portion and a second cavity is in the second height portion. An abradable coating is over the radially inner side and fills the first and second cavities.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: February 23, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: James Tilsley Auxier
  • Patent number: 10927710
    Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks. The forward and aft hooks support the blade outer air seal. The blade outer air seal is formed with a central web. The forward and aft hooks extending from the central web at a T-joint. There is a pair of mating inner laminate at the T-joint each having an axially extending portion and a vertically extending portion. The pair of mating inner laminates have an interwoven connection. A method is also disclosed.
    Type: Grant
    Filed: September 26, 2018
    Date of Patent: February 23, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Ken F. Blaney, Thomas E. Clark, Daniel J. Whitney
  • Patent number: 10920618
    Abstract: An interface assembly for a gas turbine engine. The interface a full-hoop vane ring around the engine axis, the full-hoop vane ring comprises an aft vane rail with a vane ring contact surface, the aft vane rail engaged with the anti-rotation case slot at a vane ring anti-rotation tab; and a multiple of BOAS segments around the engine axis, each of the multiple of BOAS segments comprise a BOAS forward engagement feature and a BOAS contact surface, the BOAS forward engagement feature engaged with the outer case, the BOAS contact surface abuts the vane ring contact surface.
    Type: Grant
    Filed: November 19, 2018
    Date of Patent: February 16, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Patent number: 10907505
    Abstract: A method of assembling a turbine for a turbine engine that includes mounting annular sectors around the blades to form an abradable ring that includes a groove in a sector of the annular sectors. The method also includes engaging a first wiper of a particular blade of the blades with the groove of the sector. The method further includes axially engaging an assembly comprising the blades and the annular sectors in a casing of a turbine, so that fixing members of the annular sectors cooperate with flanges of the casing to fix the annular sectors in the casing, around the blades. The fixing members comprise at least one upstream fixing member fixed on a radially internal facing side of an upstream end of the annular sectors and at least one downstream fixing member arranged at a downstream end of the annular sectors.
    Type: Grant
    Filed: November 14, 2017
    Date of Patent: February 2, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Jean-Baptiste Vincent Desforges, Gaël Frédéric Claude Cyrille Evain
  • Patent number: 10890072
    Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extend along an axial chord between a leading edge and a trailing edge. A first profiled region protrudes from the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall along the leading edge of the second side of the second airfoil adjacent the leading edge of the second airfoil. A third profiled region recessed into the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil.
    Type: Grant
    Filed: April 5, 2018
    Date of Patent: January 12, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Wolfgang Balzer
  • Patent number: 10876423
    Abstract: A gas turbine engine includes a shroud with an abradable section and a non-abradable section that cooperatively define a shroud surface. The gas turbine engine also includes a rotor that is supported for rotation within the shroud to generate an aft axial fluid flow. The rotor includes a blade with a blade tip that is crowned and that opposes the abradable section and the non-abradable section of the shroud surface. A crown area of the blade tip opposes the abradable section. A casing treatment feature is provided in the non-abradable section of the shroud to oppose the blade tip of the rotor.
    Type: Grant
    Filed: December 28, 2018
    Date of Patent: December 29, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Nick Nolcheff
  • Patent number: 10876421
    Abstract: There is provided a rotary machine including a rotary shaft configured to rotate around an axis; rotor blades; a casing surrounding the rotor blades radially outside the rotor blades, and in which a recessed portion accommodates tips of the rotor blades; a sealing portion extending from one of a bottom portion of the recessed portion and the tip of the rotor blade, and having a clearance with the other; and a variable breaker installed in the casing and is capable of being displaced between a protrusion position where the variable breaker protrudes into the recessed portion and an accommodation position where the variable breaker is accommodated in the casing.
    Type: Grant
    Filed: February 21, 2019
    Date of Patent: December 29, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Kazuyuki Matsumoto
  • Patent number: 10859011
    Abstract: A combustor includes a flow guide installed in an air channel to simultaneously implement collision cooling and convection cooling of a combustor liner and a transition piece. The air channel is formed by an inner casing and an outer casing which are spaced apart from each other by a predetermined distance, through which combustion air is introduced to the combustor in order to produce a fuel-air mixture. The flow guide is attached to an inner surface of the outer casing and extending a predetermined length towards the inner casing so as to guide the combustion air flowing through the air channel toward a surface of the inner casing. The flow guide includes a channel inlet formed on an upstream side; a channel outlet formed on a lower surface facing the inner casing; and a guide channel communicating with each of the channel inlet and the channel outlet.
    Type: Grant
    Filed: March 7, 2019
    Date of Patent: December 8, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventors: Dong Gon Lee, U Jin Roh
  • Patent number: 10830079
    Abstract: An assembly including a sector of fixed blades for turbomachine distributor including at one circumferential end a protuberance and at another circumferential end a contact surface, such that the protuberance of a sector arrives opposite the contact surface of another adjacent sector, a detachable cap including a surface with anti-wear material, configured to be engaged detachably on the protuberance of the sector, such that the anti-wear material is in contact with the contact surface of the other sector.
    Type: Grant
    Filed: October 30, 2018
    Date of Patent: November 10, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jean-Charles Marcel Bernard Coetard, Josserand Jacques Andre Bassery, Raphael Jean Philippe Dupeyre, Etienne Leon Francois
  • Patent number: 10822986
    Abstract: Turbine shrouds including internal cooling passages are disclosed. The shrouds may include a unitary body including a support portion, an intermediate portion formed integral with and extending from the support portion, and a seal portion formed integral with the intermediate portion, opposite the support portion. The unitary body may also include two opposing slash faces extending between the support portion and the seal portion, a HGP seal slot formed on each of the two opposing slash faces, and at least one plenum and cooling passage extending through the support portion, intermediate portion, and/or the seal portion. The unitary body may also include an exhaust channel and slash face exhaust holes formed in each of the two opposing slash faces. The exhaust channel may be in fluid communication with the cooling passage(s), and the slash face exhaust holes may be in fluid communication with the exhaust channel.
    Type: Grant
    Filed: January 31, 2019
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Zachary John Snider, David Wayne Weber
  • Patent number: 10822964
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes a seal ring body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a segmented spline that extends from the radially outer face of the seal ring body, the seal secured to the radially inner face of the seal ring body.
    Type: Grant
    Filed: November 13, 2018
    Date of Patent: November 3, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Patent number: 10815808
    Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the cooling of at least portions of a turbine bucket. In one embodiment, the invention provides a method of cooling at least a portion of a turbine bucket, the method comprising: during operation of a turbine, altering a swirl velocity of purge air between a platform lip extending axially from the platform and an angel wing extending axially from a face of a shank portion of the turbine bucket, wherein altering the swirl velocity of the purge air includes interrupting a flow of the purge air with a plurality of turbulators disposed along at least one of a radially inner surface of the platform lip or the face of the shank portion.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Soumyik Kumar Bhaumik
  • Patent number: 10815810
    Abstract: A blade outer air seal assembly may comprise a blade outer air seal segment and a blade outer air seal support coupled to the blade outer air seal segment. The blade outer air seal segment may comprise a forward rail and an aft rail. The forward rail may be castellated. The blade outer air seal support may comprise an aft flange and a first forward flange. A pin may be disposed through the aft rail, the aft flange, the first forward flange, and the forward rail.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William M. Barker, Daniel J. Whitney, Michael G. McCaffrey, Thomas E. Clark
  • Patent number: 10815827
    Abstract: A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.
    Type: Grant
    Filed: January 25, 2016
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Anthony B. Swift, Ken F. Blaney, Paul M. Lutjen, Neil L. Tatman, Dominic J. Mongillo
  • Patent number: 10794206
    Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. A flow guide has a plurality of flow guide segments arranged between the blade outer air seal and the support structure. An intersegment seal is at a circumferential end of at least one of the flow guide segments.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: October 6, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Patent number: 10787925
    Abstract: A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: September 29, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: David J. Thomas, Joseph P. Lamusga, Ted J. Freeman, Andrew J. Lazur
  • Patent number: 10781716
    Abstract: A cooling scheme for a blade outer air seal includes a perimeter cooling arrangement configured to convectively cool a perimeter of the blade outer air seal, and a core cooling arrangement configured to cool a central portion of the blade outer air seal through impingement cooling and to provide film cooling to an inner diameter face of the blade outer air seal.
    Type: Grant
    Filed: January 21, 2019
    Date of Patent: September 22, 2020
    Assignee: United Technologies Corporation
    Inventors: Susan M. Tholen, Dominic J. Mongillo, Paul M. Lutjen, James N. Knapp, Virginia L. Ross, Jonathan J. Earl, Eric A. Hudson
  • Patent number: 10760441
    Abstract: The invention relates to a turbine for a turbine engine, having a stator and a rotor comprising a rotor wheel having vanes the radially external periphery of which comprises at least one lip which radially extends outwards, with sealing means radially extending about the vanes and comprising a ring. The radially external end of the lip cooperates with said ring so as to form a seal of the labyrinth type.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: September 1, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Olivier Arnaud Fabien Lambert, Franck Robert Drouet, Gaël Frédéric Claude Cyrille Evain
  • Patent number: 10746042
    Abstract: An objective-driven system for blade tip clearance control may comprise a BOAS and a controller in operable communication with the BOAS. A tangible, non-transitory memory may be configured to communicate with the controller, the tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an operating objective definition, and modulating a location of the BOAS using an optimization loop comprising the operating objective definition, input vector variables, and output vector variables driven by the input vector variables.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: August 18, 2020
    Assignee: RAYTHEON TECHNOLOGYIES CORPORATION
    Inventors: Leo J. Veilleux, Jr., Thomas O. Harris, Lubomir A. Ribarov
  • Patent number: 10746054
    Abstract: A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity.
    Type: Grant
    Filed: January 16, 2019
    Date of Patent: August 18, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature High Composites Inc., Rolls-Royce North American Technologies, Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Robert J. Shinavski, Zacheriah A. Cole
  • Patent number: 10731480
    Abstract: A turbine blade assembly may be provided for use in a gas turbine engine. The turbine blade assembly may include an airfoil and a tip shroud. The airfoil may extend radially outward from an axis of rotation of the airfoil. The tip shroud may be located at a radial end of the airfoil. The tip shroud may include a seal rail that extends in a direction of rotation of the airfoil. A notch, including a Z-notch or a V-notch, may be situated on a first side of the seal rail at an end of the seal rail. A variable fillet may be situated on a second side of the seal rail that is opposite of the first side on which the notch is situated. The variable fillet is a fillet having a curvature that varies along a length of the second side.
    Type: Grant
    Filed: March 14, 2018
    Date of Patent: August 4, 2020
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Sivaram Surya Sanyasi Adavikolanu, Gayathri Puram
  • Patent number: 10731661
    Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. At least a portion of the nacelle inner surface extends radially inwardly to be radially inward of an outer diameter of the fan blades. The inner surface of the nacelle is formed with a trench, which extends into the inner surface to a radially outer extent that is spaced radially outward of the outer diameter of the fan blades.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: August 4, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, David A. Welch
  • Patent number: 10718226
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a strip seal.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: July 21, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jeffrey Walston, David J. Thomas
  • Patent number: 10718216
    Abstract: An airfoil for a gas turbine engine including a tip extension disposed at the tip of the airfoil body. The tip extension extends from the suction side surface and/or the pressure side surface and defines a tip thickness that is larger than a true thickness of the airfoil body. The true thickness is defined within a plane perpendicular to a root axis and extending transversely to the airfoil chord around a midpoint thereof. The tip extension includes a side transitional surface forming a curve extending tangentially from the side surface and/or the pressure side surface. The tip thickness increases over a radial dimension in the plane that is at least 2 times the true thickness.
    Type: Grant
    Filed: August 30, 2018
    Date of Patent: July 21, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sean Rockarts, Peter Townsend
  • Patent number: 10704407
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes an attachment feature and a body. The attachment feature and the body are constructed of ceramic matrix composite materials. In an illustrative embodiment, the ceramic matrix composite materials form a blade track segment.
    Type: Grant
    Filed: April 11, 2018
    Date of Patent: July 7, 2020
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce North American Technologies Inc.
    Inventors: Chris Barrett, Joseph P. Lamusga, Ted J. Freeman
  • Patent number: 10648339
    Abstract: A blade/vane cascade segment for a blade/vane cascade of a turbomachine includes a stage and at least two blade/vane elements that define a blade/vane intermediate strip with an axial cascade span on the stage surface by their leading and trailing edges. A stage edge on the inflow side has a contour with a depression. In the axial direction, this depression extends at most by 10% of the cascade span into the blade/vane intermediate strip. Also provided is a corresponding stage, a blade/vane cascade, a blade/vane channel, and a turbomachine.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: May 12, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Inga Mahle, Markus Brettschneider, Fadi Maatouk
  • Patent number: 10634010
    Abstract: A blade outer air seal assembly contains a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The support structure has a first support member that engages a first axial side of the blade outer air seal. A second support member engages a second axial side of the blade outer air seal. A retaining clip secures the blade outer air seal to the support structure. The retaining clip has a first leg and a second leg that extends in a generally radial direction. The first leg abuts the first axial side and the second leg abuts the first support member.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: April 28, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Patent number: 10619504
    Abstract: A blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.
    Type: Grant
    Filed: October 31, 2017
    Date of Patent: April 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Terence P. Tyler, Thurman Carlo Dabbs, Kevin J. Ryan, Nathan K. Galle
  • Patent number: 10605086
    Abstract: A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.
    Type: Grant
    Filed: November 20, 2012
    Date of Patent: March 31, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: George E. Zurmehly, Milton Ortiz, Kin Poon, Michael Vinup, Ardeshir Riahi
  • Patent number: 10584607
    Abstract: A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: March 10, 2020
    Assignee: United Technologies Corporation
    Inventor: Dmitriy A. Romanov
  • Patent number: 10570773
    Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.
    Type: Grant
    Filed: December 13, 2017
    Date of Patent: February 25, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Remy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
  • Patent number: 10557363
    Abstract: A sealing structure that seals a clearance between an outer peripheral surface of a rotor and an inner peripheral surface of a stator. The sealing structure includes: a plurality of step portions that are provided on a first surface which is one of the outer peripheral surface of the rotor and the inner peripheral surface of the stator so as to be arranged in the axial direction, and that protrude from the first surface toward a second surface which is the other of the outer peripheral surface of the rotor and the inner peripheral surface of the stator; and a seal fin that is provided on the second surface, and that forms a small clearance between a corresponding peripheral surface of the step portions. A portion in the vicinity of a tip of the seal fin in the radial direction is inclined toward the upstream side.
    Type: Grant
    Filed: February 23, 2015
    Date of Patent: February 11, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Kazuyuki Matsumoto, Yoshihiro Kuwamura, Hiroharu Oyama, Yoshinori Tanaka
  • Patent number: 10557365
    Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
    Type: Grant
    Filed: October 5, 2017
    Date of Patent: February 11, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Jeffrey M. Crutchfield
  • Patent number: 10550699
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor having a pretrench that receives at least a portion of a tip of a stator, the portion of the tip extending radially into the pretrench.
    Type: Grant
    Filed: February 13, 2014
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Ioannis Alvanos
  • Patent number: 10550710
    Abstract: A turbine shroud segment including: a target exterior surface and target interior region; and a cooling configuration having first and second channel types. The first channel type includes: an inlet and outlet; a target section extending through the target interior region; lateral ports spaced lengthwise between first and second ends of the target section; and a path within the target interior region offset from the target exterior surface by a minimum offset. The second channel type includes: dead-ends disposed at first and second ends; lateral ports connecting to lateral ports of the first channel type; and a path through the target interior region that is variable between valleys and peaks. The second channel type resides closer to the target exterior surface at the valleys than at the peaks. At each of the valleys, the second channel type resides within the minimum offset.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: February 4, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Brad Wilson VanTassel, Evan Andrew Sewall, Travis J Packer
  • Patent number: 10513934
    Abstract: A turbine blade includes an airfoil having a tip shroud. The tip shroud has an edge, and the edge has a profile substantially in accordance with values of X and Y in a Cartesian coordinate system set forth in Table 1 at points 1-30. The X and Y values represent distances that may be proportionally scaled by a common multiplier which, once scaled and connected, define the profile of the edge of the tip shroud. The profile of the edge lies in an envelope within +/?20%, +/?10% or +/?0% in a direction normal to any location along the edge set forth by the points in Table 1.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: December 24, 2019
    Assignee: General Electric Company
    Inventors: William Scott Zemitis, Antonio Rodriguez, Jason Adam Neville
  • Patent number: 10508563
    Abstract: A stator heat shield segment for a gas turbine includes an inner surface facing a hot gas main flow of the gas turbine; an outer surface opposite to the inner surface and at least partially exposed to cooling air; a first impingement cavity provided with a plurality of first impingement holes fluidly connected with the cooling air supplied outside the outer surface; a feeding cavity isolated from the cooling air supplied outside the outer surface and fluidly connected with first impingement cavity; and a second impingement cavity provided with a plurality of second impingement holes fluidly connected to the feeding cavity.
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: December 17, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Magali Cochet, Andrey Sedlov, Maxim Plodistyy
  • Patent number: 10502082
    Abstract: A turbine ring assembly includes both a plurality of CMC ring sectors forming a turbine ring and a ring support structure, each ring sector having a portion forming an annular base that presents an outside face in the radial direction of the turbine ring, with first and second attachment tabs projecting therefrom in the radial direction, each attachment tab presenting an end that is free, each ring sector having third and fourth attachment tabs, each extending in the axial direction of the turbine ring between the free end of the first attachment tab and the free end of the second attachment tab. Each ring sector is fastened to the ring support structure by a bolt having a bolt head bearing against the ring support structure and a thread co-operating with tapping formed in a plate, the plate co-operating with the third and fourth attachment tabs.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: December 10, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Nicolas Paul Tableau
  • Patent number: 10495111
    Abstract: A compressor stage of a gas turbine engine is provided. The compressor stage has a circumferential row of static vanes and a radially outer casing. Each vane has a radially outer and forwardly projecting front tenon which on build of the compressor stage is received into a first recess of the casing. Each vane also has a radially outer and rearwardly projecting rear tenon which on build of the compressor stage is received into a second recess of the casing. Each vane further has a baulking tab adjacent one of the front and the rear tenons. The casing has a respective baulking land adjacent the recess into which the other of the front and the rear tenons is received. The baulking tab and the baulking land are configured such that if the vane is attempted to be installed in the stage back-to-front, the baulking tab interferes with the baulking land to prevent completion of the build of the compressor stage.
    Type: Grant
    Filed: October 26, 2017
    Date of Patent: December 3, 2019
    Assignee: ROLLS-ROYCE PLC
    Inventor: Lee Nithsdale
  • Patent number: 10487677
    Abstract: A method of forming a structure in a turbine component having a seal slot, the slot including walls defining an opening therebetween, the method includes the step of using an additive manufacturing process to form a neck structure on a wall so as to reduce a size of the opening.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: November 26, 2019
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Victor Hugo Silva Correia
  • Patent number: 10479514
    Abstract: An assembly for an aircraft turbine machine including a receiver for a pair of open rotor contra-rotating propellers, the assembly including a duct, ancillaries routed inside the duct, an attachment case, attachment device of the duct on an annular installation portion of the case. The attachment device in an assembled configuration include a split ring fitted with internal projections housed inside orifices in the duct; a radial loading surface of the ring made on the portion the surface being tapered and narrowing along a first axial direction, and being in contact with a peripheral surface of the complementary shaped tapered split ring; device of axially loading the ring along the first direction, the device being blocked in the axial direction on the portion.
    Type: Grant
    Filed: January 4, 2017
    Date of Patent: November 19, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clementine Charlotte Marie Mouton, Olivier Belmonte, Jeremy Phorla Lao, Didier Jean-Louis Yvon
  • Patent number: 10472986
    Abstract: An aircraft jet propulsion system may comprise a thermoelectric cooler array coupled to a portion thereof, wherein the TEC array converts electrical energy to heat energy to create a temperature gradient and cools a turbine case using the temperature difference of the TEC array. The system may include a controller configured to control an input power provided to each TEC of the array of TECs, such that the array of TECs facilitates controlled cooling of the aircraft jet propulsion system in response to the input power provided to each TEC of the array of TECs. The TEC array may be powered by an alternator or by a thermoelectric generator.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: November 12, 2019
    Assignee: United Technologies Corporation
    Inventor: John Akin