Patents Examined by Justin A Pruitt
  • Patent number: 11041392
    Abstract: An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.
    Type: Grant
    Filed: September 22, 2017
    Date of Patent: June 22, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Jesse M. Carr, Bryan P. Dube
  • Patent number: 11041394
    Abstract: Joining an airfoil with a platform by mechanical keying can provide advantages in applications of ceramic materials, such as ceramic matrix composites.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: June 22, 2021
    Assignees: Rolls-Royce Corporation
    Inventors: Jeffrey A. Walston, Michael Whittle, Daniel K. Vetters, Eric Koenig
  • Patent number: 11041504
    Abstract: A rotor for a centrifugal compressor includes: a rotor main; an impeller; and a contact member. The rotor main body extends in an axis direction and includes a recessed part that is disposed on an outer circumferential surface. The impeller includes: a cylinder part having a cylindrical shape that extends around the axis direction and includes an inner circumferential surface with a fitting region tightly fitted to the outer circumferential surface of the rotor main body; an annular disc that extends from the cylinder part to a radial outer side with respect to the axis direction; a plurality of blades disposed at intervals in a circumferential direction on a surface facing one side in the axis direction of the annular disc; and a cover that covers the plurality of blades from the one side in the axis direction. The contact member is fitted into the recessed part.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: June 22, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventor: Shinichiro Tokuyama
  • Patent number: 11028722
    Abstract: The present disclosure is directed to a blade track assembly used in a gas turbine engine. The blade track assembly includes blade track segments made from ceramic matrix composite materials and a tip clearance control system for adjusting the inner diameter of the blade track assembly during use in an engine.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: June 8, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Patent number: 11015460
    Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).
    Type: Grant
    Filed: August 2, 2016
    Date of Patent: May 25, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Matthieu Arnaud Gimat, Alain Jacques Michel Bassot, Jérémy Guivarc'h, Jean-Noël Mahieu, Thibault Ruf
  • Patent number: 11002143
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: September 20, 2018
    Date of Patent: May 11, 2021
    Assignees: Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Peter Broadhead, Steven Hillier
  • Patent number: 11002138
    Abstract: A turbine blade having a base and an airfoil, the base including cooling air inlets and an internal cooling air passageway, and the airfoil including an internal multi-bend heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, and a tip flag cooling system.
    Type: Grant
    Filed: September 7, 2018
    Date of Patent: May 11, 2021
    Assignee: Solar Turbines Incorporated
    Inventors: Andrew T. Meier, Nnawuihe Okpara, Stephen Edward Pointon, Hans D. Hamm, Kevin Hirako
  • Patent number: 10989069
    Abstract: A steam turbine cooling unit for a steam turbine includes a coolant steam path provided to penetrate a casing along a superheated steam supply tube to reach a gap; and a coolant steam supplying unit configured to supply coolant steam flowing through the coolant steam path along the superheated steam supply tube to reach the gap, and having: (i) a pressure higher than a pressure of superheated steam to be supplied by the superheated steam supply tube; and (ii) a temperature lower than a temperature of the superheated steam to be supplied by the superheated steam supply tube.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: April 27, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Takumi Matsumura, Toyoharu Nishikawa, Katsuhisa Hamada
  • Patent number: 10927677
    Abstract: Airfoil assemblies for gas turbine engines are provided. For example, an airfoil assembly comprises an airfoil, an inner band defining an inner opening shaped complementary to an inner end of the airfoil, and an outer band defining an outer opening shaped complementary to an outer end of the airfoil. The airfoil inner end is received with the inner opening, and the airfoil outer end is received within the outer opening. A strut extends radially through an airfoil cavity. A first pad is defined at a first radial location within the cavity. A second pad is defined within the cavity at a second, different radial location. In some embodiments, the airfoil assembly inner band includes a first inner flange, through which the inner band is secured to a support structure, and the outer band includes a first outer flange, through which the outer band is secured to a support structure.
    Type: Grant
    Filed: March 15, 2018
    Date of Patent: February 23, 2021
    Assignee: General Electric Company
    Inventors: Darrell Glenn Senile, Matthew Mark Weaver, Alexander Martin Sener
  • Patent number: 10920610
    Abstract: A casting plug for a vane of a gas turbine engine includes a plug body a flow control feature and a support that extends between the plug body and the flow control feature.
    Type: Grant
    Filed: June 11, 2018
    Date of Patent: February 16, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Jaime G. Ghigliotty
  • Patent number: 10883372
    Abstract: A gas turbine component, for forming part of a stage of the turbine, operable to change cooling scheme, includes an airfoil profiled section, a cooling passageway, film holes and interchangeable connectors. The profiled section includes pressure and suction sides joined together at chordally opposite leading and trailing edges. The cooling passageway extends between the pressure and suction sides along the leading edge to enabling cooling fluid to flow therefrom. The film holes are configured on the cooling passageway to enable the flow of a portion of the cooling fluid to a portion of the profiled section. The interchangeable connectors configured to the cooling passageway, one at a time, to change the cooling scheme. An insert may also be provided to close and open the film holes.
    Type: Grant
    Filed: January 26, 2015
    Date of Patent: January 5, 2021
    Assignee: General Electric Technology GMBH
    Inventors: Joergen Ferber, Petr Vitalievich Laletin
  • Patent number: 10876536
    Abstract: A compressor includes impellers each having its chord angle less than its stall angle. The impellers can be used in a contra-rotating impeller arrangement without static diffusers. The contra-rotating impeller arrangement provides for much larger nominal flow rates than conventional single rotating impeller arrangements with the same chord angles. Accordingly, a surge free design is provided without excessively compromising the nominal flow rate. Techniques for enhancing stall characteristics of the impellers are also described.
    Type: Grant
    Filed: July 23, 2015
    Date of Patent: December 29, 2020
    Assignee: ONESUBSEA IP UK LIMITED
    Inventor: Bernt-Helge Torkildsen
  • Patent number: 10865804
    Abstract: Provided is a centrifugal compressor impeller that includes blades extending from an inlet to an outlet for a fluid. Each of the blades of the impeller includes, when a distribution of blade angles of a tip is viewed in a direction in which the tip extends from a tip inlet to a tip outlet for the tip, a constant blade angle region in which the blade angles are constant. A start point on the inlet side of the constant blade angle region is set at a position spaced apart from the tip inlet.
    Type: Grant
    Filed: February 1, 2017
    Date of Patent: December 15, 2020
    Assignee: IHI Corporation
    Inventors: Chihiro Mikami, Ryuuta Tanaka
  • Patent number: 10836478
    Abstract: A rotor actuation system includes a swashplate assembly comprised of a stationary swashplate and a rotating swashplate operatively connected together for relative rotation about a rotor axis. A cyclic actuator is operatively connected to the stationary swashplate to tilt the swashplate assembly off axis from the rotor axis for cyclic control. A collective actuator is operatively connected to the swashplate assembly to move the swashplate axially along the rotor axis for collective control. The cyclic actuator and the collective actuator are operatively connected to the swashplate assembly to respectively actuate cyclic and collective control independent of one another.
    Type: Grant
    Filed: August 24, 2016
    Date of Patent: November 17, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Lance Halcom
  • Patent number: 10823189
    Abstract: A hot air feed wheel, for a vehicle heater, includes a hub (44) to fix the hot air feed wheel (22) to a drive shaft and a feed area (50), adjacent to the hub (44), in a transition area (48). A plurality of feed blades (36) are arranged following one another about a feed wheel longitudinal axis (L) in the circumferential direction. The transition area (48) includes a plurality of connection webs (66) following one another about the feed wheel longitudinal axis (L) in the circumferential direction.
    Type: Grant
    Filed: January 11, 2018
    Date of Patent: November 3, 2020
    Assignee: Eberspächer Climate Control Systems GmbH & Co. KG
    Inventors: Michael Haefner, Hans Jensen, Oleg Dering, Henry Rösch
  • Patent number: 10815787
    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.46-0.59 inch (11.8-14.9 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133±15% Hz, a second mode with a frequency of 8542±15% Hz, a third mode with a frequency of 15487±15% Hz, a fourth mode with a frequency of 18774±15% Hz, a fifth mode with a frequency of 24295±15% Hz and a sixth mode with a frequency of 27084±15% Hz.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: David Mikol, Kimberly Pash Boyington, Brian J. Schuler, Zhen Wu, Joseph Wieser, Xuedong Zhou, Sue-Li Chuang, John Joseph Papalia, Han J. Yu
  • Patent number: 10781827
    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 27.5-28.5 inches (699-724 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34±10% Hz, a second mode with a frequency of 90±10% Hz, a third mode with a frequency of 178±10% Hz, a fourth mode with a frequency of 222±10% Hz, a fifth mode with a frequency of 307±10% Hz and a sixth mode with a frequency of 389±10% Hz.
    Type: Grant
    Filed: January 16, 2018
    Date of Patent: September 22, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jason Elliott, Daniel C. Falk, Myron L. Klein, Ethan C. Drew, James H. Moffitt, Darryl Whitlow, Byron R. Monzon, Jay Thomas Abraham, William R. Graves
  • Patent number: 10767558
    Abstract: A particle separator adapted for use with a gas turbine engine includes an inner wall, an outer wall, and a splitter. The splitter cooperates with the inner wall and the outer wall to separate particles suspended in an inlet flow moving through the particle separator to provide a clean flow of air to the gas turbine engine.
    Type: Grant
    Filed: March 7, 2018
    Date of Patent: September 8, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Crawford F. Smith, III, Bryan H. Lerg
  • Patent number: 10753213
    Abstract: The invention relates to a wear-resistant shield for a rotating blade root of a rotating blade of a gas turbine, especially an aircraft gas turbine, having a base and two side walls connected to the base, wherein the side walls lie opposite each other and are shaped so as to be substantially complementary to an outer contour of a particular rotating blade root, and wherein the wear-resistant shield for this purpose is set up in such a way that, in an installed state, it is to be taken up between the respective rotating blade root and a rotating blade root mount of a rotor, especially between the respective rotating blade root and an axial securing element arranged in the rotating blade root mount.
    Type: Grant
    Filed: April 27, 2018
    Date of Patent: August 25, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Martin Pernleitner, Rudolf Stanka, Manfred Dopfer
  • Patent number: 10746210
    Abstract: An assembly of a first element with a second element includes an elongate thin lip belonging to the second element being inserted in an elongate narrow slot formed by three sides of an elongate flat plate fixed in parallel to a flat wall of the first element. At least one element forming a guide is secured to a long side of the elongate flat plate forming an edge of the slot. The element forming a guide includes a sliding surface extending in the continuation of the elongate flat plate and diverging from the flat wall away from the first element. The at least one element forming a guide cooperates with the lip so that the insertion of the lip into the slot begins with the sliding of the lip on the sliding surface and then continues as the lip advances, with progressive insertion of the lip into the slot.
    Type: Grant
    Filed: September 30, 2014
    Date of Patent: August 18, 2020
    Assignee: RENAULT s.a.s.
    Inventors: Pascal David, Joseph Bui