Between Blade Edge And Static Part Patents (Class 415/173.1)
  • 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
  • Patent number: 10458268
    Abstract: A turbine shroud adapted to extend around a bladed turbine wheel to block gasses from passing over the bladed turbine wheel is disclosed. In a segmented embodiment, each turbine shroud segment may include a carrier segment and a blade track segment. The carrier segment may comprise metallic materials and may be formed to define an attachment-receiving space. The blade track segment may comprise ceramic matrix composite materials and may be formed to include an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment.
    Type: Grant
    Filed: April 13, 2016
    Date of Patent: October 29, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Mark O'Leary
  • Patent number: 10458263
    Abstract: A segmented turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and retainers. The blade track is mounted onto the retainers, and the retainers are attached to the carrier to support the blade track radially outside of the blades.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: October 29, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Patent number: 10458427
    Abstract: A compressor aerofoil for a turbine engine or an axial process compressor, the compressor aerofoil includes a suction surface wall having a suction surface and a pressure surface wall having a pressure surface, the suction surface wall and the pressure surface wall meet at a leading edge and a trailing edge and define a tip having a tip surface, the aerofoil has a maximum thickness Tmax. A mean camber line is defined as passing through the leading edge and the trailing edge. The compressor aerofoil further includes a winglet at the tip and which extends from the suction surface, the winglet has an overhang W that has a perpendicular extent from the suction surface in the range 0.1Tmax to 1.5Tmax. The winglet has a maximum overhang Wmax that occurs within 50% of the length of the mean camber line from the leading edge.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: October 29, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: John McGill, Robert Miller, Roger Wells
  • Patent number: 10443427
    Abstract: Method for repairing a turbine-engine component, such as a turbine nozzle (D), this component comprising an annular wall for supporting an abradable ring (C2), the method comprising first-repair steps (I) consisting in: removing a first abradable ring (C2), the brazing for fixing the ring to the annular wall, and an inner peripheral part of the annular wall, and fixing a second abradable ring (C2) to the annular wall by brazing, characterized in that the second abradable ring has finished dimensions (r1?), the first repair not having a step of grinding of the second ring after fixing thereof to the annular wall.
    Type: Grant
    Filed: June 15, 2015
    Date of Patent: October 15, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Guillaume Mongis, Guillame Benoit Noel Champion, Pascal Jean-Serge Drouard
  • Patent number: 10443616
    Abstract: A seal system includes a segmented annular seal support that has carriage arc segments arranged circumferentially in circumferential carriage joints, and a segmented annular seal that includes seal arc segments arranged end-to-end in circumferential seal joints. The circumferential seal joints are circumferentially offset from the circumferential carriage joints.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 10443435
    Abstract: A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Richard K. Hayford, Michael J. Bruskotter, Ross A. Vandenbosch
  • Patent number: 10443405
    Abstract: A rotor blade includes an airfoil. The airfoil includes a leading edge and a trailing edge downstream of the leading edge. The airfoil also includes a radially outer tip with a pressure side tip rail and a suction side tip rail. A slot is formed in an aft portion of the suction side tip rail and an opening is positioned between the suction side tip rail and the pressure side tip rail at the trailing edge. Gas flows from the tip via the slot and the opening to inhibit formation of a vortex flow proximate to the suction side of the airfoil.
    Type: Grant
    Filed: May 10, 2017
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: Moorthi Subramaniyan, Adam John Fredmonski
  • Patent number: 10435178
    Abstract: A holding fixture includes a first blade support assembly and a second blade support assembly. The second blade support assembly is spaced at a distance from the first blade support assembly and includes a base plate removably mounted to a milling machine, an adjustable conic support connectable to the base plate via a spacer block, and a blade adjustment assembly movable to control a pressure applied by the blade adjustment assembly.
    Type: Grant
    Filed: September 30, 2016
    Date of Patent: October 8, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Sven Roy Lofstrom, David Littlejohn
  • Patent number: 10400619
    Abstract: A shroud hanger assembly or shroud assembly is provided for a gas turbine engine wherein a hanger includes a radially depending and axially extending arm. The arm or retainer engages a pocket formed in a shroud so as to retain the shroud in a desired position relative to the hanger. An aft retaining structure is provided on the hanger and provides a seat for a seal structure which biases the retainer so that the arm of the hanger maintains engagement in the shroud pocket. A baffle may be utilized at the hanger to cool at least some portion of the shroud.
    Type: Grant
    Filed: May 5, 2015
    Date of Patent: September 3, 2019
    Assignee: General Electric Company
    Inventors: Jason David Shapiro, Jonathan David Baldiga
  • Patent number: 10400620
    Abstract: Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.
    Type: Grant
    Filed: August 4, 2016
    Date of Patent: September 3, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Lubomir A. Ribarov, Charles W. Haldeman
  • Patent number: 10392957
    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: August 27, 2019
    Assignee: Rolls-Royce Corporation
    Inventor: Jeffrey M. Crutchfield
  • Patent number: 10393149
    Abstract: The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.
    Type: Grant
    Filed: March 2, 2017
    Date of Patent: August 27, 2019
    Assignee: General Electric Company
    Inventors: Bhaskar Nanda Mondal, Kenneth Edward Seitzer, Monty Lee Shelton, Thomas Ory Moniz, Atanu Saha
  • Patent number: 10385700
    Abstract: A turbomachine turbine blade includes a suction face, a pressure face, a leading edge and a trailing edge as well as a squealer at the tip thereof. The squealer tip includes at least one internal rib that extends from a point of attachment of the rim of the squealer on the suction-face side to a point of attachment of the rim of the squealer on the pressure-face side, and includes a portion for absorbing the load of leakage flows which extends from the suction face and a deflector-forming portion which extends the load absorber portion with an inflection and guides the leakage flows toward the pressure face.
    Type: Grant
    Filed: August 3, 2015
    Date of Patent: August 20, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pierre Guillaume Auzillon, Remi Philippe Oswald Olive, Marjolaine Marie-Anne Pierre
  • Patent number: 10385709
    Abstract: Flow path assemblies having features for positioning the assemblies within a gas turbine engine are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes an integral combustion portion and turbine portion, the combustor portion extending through a combustion section of the gas turbine engine and the turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The flow path assembly further comprises at least two positioning members for radially centering the flow path assembly within the gas turbine engine. The positioning members extend to the flow path assembly from one or more structures external to the flow path assembly, constrain the flow path assembly tangentially, and allow radial and axial movement of the flow path assembly. Other embodiments for positioning flow path assemblies also are provided.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: Brandon Allanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher, Aaron Michael Dziech, Brett Joseph Geiser
  • Patent number: 10385731
    Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: Daniel Patrick Kerns, Mark Eugene Noe, Dennis Paul Dry, Brandon ALlanson Reynolds
  • Patent number: 10385776
    Abstract: Methods for assembling flow path structures having one or more unitary components are provided. For example, one method for assembling a flow path assembly of a gas turbine engine comprises stacking axially adjacent components within a generally annular outer wall of the flow path assembly. The flow path assembly defines a flow path through a combustion section and at least a portion of a turbine section of the gas turbine engine. The outer wall defines an outer boundary of the flow path, and the axially adjacent components defining at least a portion of an inner boundary of the flow path. The outer wall is a unitary outer wall that includes a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of the turbine section. The combustor and turbine portions are integrally formed as a single unitary structure.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: Brandon ALlanson Reynolds, Aaron Michael Dziech
  • Patent number: 10385718
    Abstract: A turbine shroud segment of a turbine shroud for use in a turbine of a gas turbine engine is disclosed herein. The turbine shroud segment includes a carrier segment and a blade track segment. The carrier segment includes metallic materials. The blade track segment includes ceramic matrix composite materials. A seal is arranged between the carrier segment and the blade track segment.
    Type: Grant
    Filed: June 7, 2016
    Date of Patent: August 20, 2019
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Mark O'Leary, Daniel K. Vetters
  • Patent number: 10378373
    Abstract: Flow path assemblies of gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and a unitary outer wall that includes a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils, each nozzle airfoil having an inner end radially opposite an outer end. The inner wall or the unitary outer wall defines a plurality of openings therethrough, and each opening is configured for receipt of one of the plurality of nozzle airfoils. Methods of assembling flow path assemblies also are provided.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Darrell Glenn Senile, Daniel Patrick Kerns, Michael Ray Tuertscher
  • Patent number: 10370997
    Abstract: A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: August 6, 2019
    Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.
    Inventors: Daniel Kent Vetters, David J. Thomas, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • Patent number: 10370990
    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and an outer wall defining an opening therethrough, as well as a nozzle airfoil having an inner end radially opposite an outer end that is positioned within the opening defined in the outer wall such that the outer end projects radially outwardly from the outer wall. The flow path assembly also comprises a pin and a first support member. The pin extends from the first support member to the outer end of the nozzle airfoil to support the nozzle airfoil. In some embodiments, the outer end of the nozzle airfoil defines a flange configured to receive the pin and a radial stop configured to press against a radially outward external support, and the pin is configured to transfer a load on the nozzle airfoil to an external structure.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: August 6, 2019
    Assignee: General Electric Company
    Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga
  • Patent number: 10371008
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: August 6, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Jeffrey A. Walston, Jun Shi
  • Patent number: 10371383
    Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: August 6, 2019
    Assignee: General Electric Company
    Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Andrew Scott Bilse, Michael Todd Radwanski, Ernesto Andres Vallejo Ruiz, Aaron Michael Dziech, Mark Eugene Noe
  • Patent number: 10364693
    Abstract: A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track.
    Type: Grant
    Filed: August 7, 2017
    Date of Patent: July 30, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: David J. Thomas, Richard C. Uskert
  • Patent number: 10344611
    Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals disposed therein, the blade outer air seals each including a body including a raised material that extends beyond the outer surface of the body and the raised material includes an inlet hole formed through the raised material.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: July 9, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Nathan K. Galle
  • Patent number: 10344771
    Abstract: The present invention relates to a turbomachine component (1) or collection of components comprising at least a first and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2) has a non-axisymmetric surface (S) bounded by a first and a second end plane (PS, PR) and defined by at least two class C construction curves each one representing the value of a radius of said surface (S) as a function of a position between the pressure face of the first blade (3I) and the suction face of the second blade (3E) in a plane substantially parallel to the end planes (PS, PR), these including at least one upstream curve and one downstream curve; each construction curve being defined by at least one pressure face control end point and one suction face control end point such that: —the tangent to the downstream curve at the suction face control end point 20 is inclined by at most 5°; —any other tangent to a construction curve at a control end point is inclined
    Type: Grant
    Filed: December 16, 2014
    Date of Patent: July 9, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benjamin Lukowski, Esteban Bernardos-Chamagne, Matthieu Jean Luc Vollebregt
  • Patent number: 10328490
    Abstract: A method of manufacturing a turbine shroud segment for a gas turbine engine comprises: metal injection molding (MIM) a shroud segment body with a groove defined in a first lateral side thereof and with a flow restrictor projecting integrally from an opposite second lateral side thereof. The groove is oversized relative to the flow restrictor to provide for a clearance fit between the flow restrictor and the groove of adjacent turbine shroud segments when assembled together in a ring formation. The shroud segment body with the integrated flow restrictor are then subjected to debinding and sintering operations.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: June 25, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Patent number: 10322575
    Abstract: Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
    Type: Grant
    Filed: July 27, 2017
    Date of Patent: June 18, 2019
    Assignee: General Electric Company
    Inventors: Benjamin Paul Lacy, Srikanth Chandrudu Kottilingam, Christopher Donald Porter, David Edward Schick
  • Patent number: 10316686
    Abstract: An actuation system according to various embodiments can include an actuation ring having a first end and a second end separated by a gap, the actuation ring being configured to be coupled to a blade outer air seal (BOAS). The actuation system can also include an actuator coupled to at least one of the first end or the second end and configured to adjust a size of the gap such that a tip clearance between the BOAS and a blade tip is reduced in response to the size of the gap being reduced.
    Type: Grant
    Filed: November 22, 2016
    Date of Patent: June 11, 2019
    Assignee: United Technologies Corporation
    Inventors: Eric A. Hudson, Stephen K. Kramer
  • Patent number: 10309252
    Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: June 4, 2019
    Assignee: General Electric Company
    Inventors: Marc Lionel Benjamin, Benjamin Paul Lacy, Dipankar Pal, San Jason Nguyen
  • Patent number: 10294862
    Abstract: A turbine engine casing flow-path segment that is locally diffusing, followed by a flow-path segment contracting in the vicinity of a fan blade. This contraction accelerates the fluid flow axially forward of the fan blade leading edge at the tip and converges with the linear flow-path aft of the fan blade leading edge but forward of the fan blade trailing edge. More diffused fluid flow results in increased flow capacity of the fan, and increased fan efficiency.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: May 21, 2019
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Roy David Fulayter, Aaron Joseph King, Bronwyn Power, Greg Hebert
  • Patent number: 10253637
    Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
    Type: Grant
    Filed: December 11, 2015
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Eric Joseph Schroeder, Paul Hadley Vitt, Timothy John Swenson, Kirk Douglas Gallier, Aspi Rustom Wadia
  • Patent number: 10221697
    Abstract: A turbine blade (100) having an airfoil (1). In its radially outer region, the turbine blade (100) has at least one shroud (200) or at least one shroud segment, as well as at least one cutting tooth (300) which is intended to engage at least once into portions of a turbine casing during use of the turbine blade (100). The cutting tooth (300) is connected to the shroud (200) or the shroud segment.
    Type: Grant
    Filed: December 10, 2013
    Date of Patent: March 5, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Alexander Boeck, Manfred Feldmann, Stephen Royston Williams
  • Patent number: 10208617
    Abstract: A carrier segment of a carrier section for circumscribing an array of circumferentially spaced turbine blades of a gas turbine engine, the blades being disposed radially inwardly of a turbine casing, the carrier segment including a carrier wall disposed radially inwardly of the casing and radially outwardly of the turbine blades, and the carrier wall including one or more portions facing the casing, wherein at least one of the one or more portions of the carrier wall is provided with one or more impingement apertures therein for passage therethrough of air of a predetermined temperature, heating air, from a feed source into impingement onto the turbine casing. The application of heating air onto the casing during transient stages of enhanced engine power, e.g. during step climbs, results in better matching of radial expansion of the casing relative to the turbine blades, thereby enabling improved blade tip clearance control.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: February 19, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Simon Lloyd Jones, Leo V. Lewis