Patents Examined by J Todd Newton
  • Variable speed boost compressor for gas turbine engine cooling air supply
    Patent number: 11268530
    Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.
    Type: Grant
    Filed: March 27, 2020
    Date of Patent: March 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: Gary D. Roberge
  • Blade outer air seal cooling fin
    Patent number: 11268402
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal 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 multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture.
    Type: Grant
    Filed: April 11, 2018
    Date of Patent: March 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Adam Lee Hart, Brian Levy, Luis Miguel Ayalde, Jose R. Paulino, Patrick Scheelk, Nicolas Bueno
  • Mid mount sleeve arrangement
    Patent number: 11268442
    Abstract: A shaft and sleeve assembly of a gas turbine engine includes an outer shaft extending about an engine central longitudinal axis and having a radially inner shaft surface. The radially inner shaft surface has a shaft groove define therein. A sleeve is located radially inboard of the radially inner shaft surface. The sleeve includes a sleeve groove defined in a radially outer sleeve surface. The sleeve groove is formed at an axial location between a first axial end and a second axial end of the sleeve. A retaining element is installed in the shaft groove and the sleeve groove to retain the sleeve relative to the outer shaft. The sleeve includes one or more sleeve openings formed therein, and the sleeve groove is aligned with the one or more sleeve openings.
    Type: Grant
    Filed: July 1, 2020
    Date of Patent: March 8, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Todd A. Davis, Paul R. Hanrahan
  • Article having variable composition coating
    Patent number: 11261742
    Abstract: A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.
    Type: Grant
    Filed: November 17, 2014
    Date of Patent: March 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Mark T. Ucasz
  • Shell for reducing overpressure in the vicinity of the upstream seal of a turbojet bearing housing
    Patent number: 11261754
    Abstract: The invention relates to a turbojet bearing housing including a fixed envelope traversed by a rotor, this envelope including a cylindrical end surrounding a seal ensuring the leak tightness of the cylindrical end of the envelope with the rotor, this envelope being equipped with a shell screwed onto the cylindrical end thereof, this shell including radial channels emerging opposite the seal while being arranged so that an air stream traversing the seal towards the housing mainly comes from these radial channels.
    Type: Grant
    Filed: February 5, 2018
    Date of Patent: March 1, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Frédéric Patard, Antoine Jean-Philippe Beaujard, Philippe Pierre Vincent Bouiller, Christophe Caplain, Maxime Aurélien Rotenberg
  • Vane with seal
    Patent number: 11261748
    Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.
    Type: Grant
    Filed: November 8, 2019
    Date of Patent: March 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Robert White, III
  • Floating, non-contact seal and dimensions thereof
    Patent number: 11255207
    Abstract: Aspects of the disclosure are directed to a seal comprising: a shoe, and at least two beams coupled to the shoe, where a first width associated with the beams exceeds a second width associated with the shoe in a reference direction. Aspects of the disclosure are directed to an engine comprising: a compressor section, a turbine section, and a floating, non-contact seal that includes: a shoe, and at least two beams coupled to the shoe, where the beams extend past an edge of a flowpath surface associated with the shoe in a reference direction.
    Type: Grant
    Filed: August 23, 2019
    Date of Patent: February 22, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: Christopher J. Peters
  • Vane arc segment platform flange with cap
    Patent number: 11255194
    Abstract: A vane arc segment includes an airfoil piece that has a first platform, a second platform, and an airfoil section between the first platform and the second platform. At least the first platform is formed of a fiber-reinforced composite (FRC) and defines a radial flange. A cap is fitted on the radial flange.
    Type: Grant
    Filed: February 11, 2020
    Date of Patent: February 22, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E. Sobanski, Bryan H. Farrar
  • Wind turbine blade having a lightning tip receptor
    Patent number: 11248588
    Abstract: A wind turbine blade comprising a main blade portion having a root end and a tip end, wherein a leading edge and a trailing edge extend between the root end and the tip end, and a conductive blade tip module that abuts the tip end of the main blade portion; wherein the conductive blade tip module comprises an elongate body defining a longitudinal axis transverse to a spanwise axis of the blade, and wherein the conductive blade tip module has a length in a direction along said longitudinal axis that is greater than a chord length of the blade tip interface.
    Type: Grant
    Filed: July 27, 2017
    Date of Patent: February 15, 2022
    Assignee: Vestas Wind Systems A/S
    Inventors: Jakob Hjorth Jensen, Lasse Lykkegaard
  • Repeating airfoil tip strong pressure profile
    Patent number: 11248622
    Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.
    Type: Grant
    Filed: September 2, 2016
    Date of Patent: February 15, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Simon W. Evans, Yuan Dong, Sean Nolan
  • Turbine housing and method of improving efficiency of a radial/mixed flow turbine
    Patent number: 11248483
    Abstract: A turbine housing for a radial/mixed flow turbine, the turbine having a rotor comprising a plurality of blades disposed about a hub, the turbine housing comprising: a shroud configured to at least partially enshroud the rotor wherein a clearance is provided between the shroud and blade tips of the plurality of blades, the shroud and the hub defining a main passage of fluid flow in the turbine; and at least one injection opening provided in the shroud, the at least one injection opening configured to allow injection of a secondary flow of fluid into at least the clearance between the shroud and the blade tips.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: February 15, 2022
    Assignee: Nanyang Technological University
    Inventors: Alessandro Romagnoli, Srithar Rajoo, Ricardo Fernando Martinez-Botas Mateo, Hao Liu
  • Turbine and turbocharger
    Patent number: 11236669
    Abstract: A turbine includes: a turbine impeller; a housing disposed so as to enclose the turbine impeller, and including a scroll passage positioned on an outer circumferential side of the turbine impeller and an inner circumferential wall part defining an inner circumferential boundary of the scroll passage; a plurality of nozzle vanes disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller; and a plate disposed on a side of the intermediate flow passage with respect to the inner circumferential wall part so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction. The plate has at least one through hole through which the intermediate flow passage and the gap are communicated with each other.
    Type: Grant
    Filed: December 20, 2017
    Date of Patent: February 1, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Bipin Gupta, Toyotaka Yoshida
  • Vertical axis wind turbine
    Patent number: 11236724
    Abstract: A vertical axis wind turbine (VAWT) with improved and optimized wind-directing, wind-shaping, and wind-power conversion features is disclosed. The shapes of these features directly affect the ability of the VAWT to use the power of moving air, such as wind, to spin a rotor and create torque on a rotor shaft to generate electricity. The wind-power-conversion mechanical efficiency of the invention is significantly improved over previous efforts, to the point that the invention can convert wind energy into electrical power at a price-to-performance ratio that competes with or surpasses existing alternative energy technologies.
    Type: Grant
    Filed: April 6, 2020
    Date of Patent: February 1, 2022
    Assignee: DME Wind Energy Corporation
    Inventors: Sid J. Reyna, Patrick R. Conarro, Douglas Bachli, Darrin Trussell
  • Method for tight control of bolt holes in fan assembly
    Patent number: 11236769
    Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.
    Type: Grant
    Filed: August 29, 2019
    Date of Patent: February 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas J. Robertson, Mark W. Costa
  • Flap arrangement for a turbine of an exhaust-gas turbocharger
    Patent number: 11236666
    Abstract: The invention concerns a flap arrangement 10 for a turbine 2 of an exhaust-gas turbocharger 2, in particular for a wastegate valve of the turbine, having a spindle 100 for rotatable mounting of the flap arrangement 10 in a turbine housing 3, a lever arm 200, the lever arm 200 being coupled to the spindle 100, and a flap plate 300, the flap plate 300 being coupled to the lever arm 200. The flap plate 300 has a flexible part 330 in a radially outer region of the flap plate 300, such that by applying a closing force to the flap arrangement 10 when the flap plate 300 is in contact with a flap seat 500 in the turbine housing 3, elastic and/or plastic deformation of the flexible part 330 of the flap plate 300 can be caused to compensate for thermal deformation of the turbine housing 3, exhaust deposits and/or wear.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: February 1, 2022
    Assignee: BorgWarner Inc.
    Inventors: Marcel Golz, Jason Robert Walkingshaw, Jens Watanpour, Anna Gilbert
  • Aircraft turbine rear structures
    Patent number: 11230943
    Abstract: A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.
    Type: Grant
    Filed: November 6, 2018
    Date of Patent: January 25, 2022
    Assignee: GKN Aerospace Sweden AB
    Inventor: Fredrik Wallin
  • System control strategy and methods for multi-physics fluid atomizing
    Patent number: 11231003
    Abstract: A method of controlling fuel delivery to an engine includes providing a fluid atomizer, a mechanically driven air compressor, a start up air source, and an air valve coupled between the mechanically driven air compressor and the start up air source, charging the start up air source, delivering compressed air from the start up air source to the fluid atomizer, providing an initial air/fluid mixture with the fluid atomizer, and operating the air valve to direct compressed air from the mechanically driven air compressor to the fluid atomizer.
    Type: Grant
    Filed: June 4, 2019
    Date of Patent: January 25, 2022
    Assignee: Enginetics, LLC
    Inventors: Roderick James Harris, Joseph Lull
  • Guide vane with truss structure and honeycomb
    Patent number: 11230928
    Abstract: A vane includes an airfoil that defines a leading edge, a trailing edge, a pressure side, and a suction side. The airfoil includes a truss structure that has ribs that define there between a plurality of through-cavities from the pressure side to the suction side. Honeycomb cells are disposed in the cavities. A face sheet defines at least one of the pressure side or the suction side. The face sheet has perforations that correspond in location to the honeycomb cells.
    Type: Grant
    Filed: July 22, 2020
    Date of Patent: January 25, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Larry Foster
  • Airfoil of axial flow machine
    Patent number: 11230934
    Abstract: An airfoil of an axial flow machine includes an airfoil part that has a suction surface and a pressure surface, an endwall as a shroud or a platform, and a fillet that is provided along a connecting portion between the airfoil part and the endwall. The fillet includes a first curved surface formed at least on a leading edge side and a trailing edge side in the airfoil part on the suction surface side and a second curved surface formed in a portion other than a portion where the first curved surface is formed. The second curved surface has a smaller curvature radius than the first curved surface.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: January 25, 2022
    Assignee: IHI Corporation
    Inventor: Masaaki Hamabe
  • Inserts for airfoils of gas turbine engines
    Patent number: 11230931
    Abstract: Baffle inserts for airfoils of gas turbine engines are described. The baffle inserts include a baffle insert body having a first side portion and a second side portion, wherein each side portion has a respective end, a first set of vortex generation elements is arranged at the end of the first side portion, and a second set of vortex generation elements is arranged at the end of the second side portion. The first set of vortex generation elements and the second set of vortex generation elements are arranged at an aft end of the baffle insert body.
    Type: Grant
    Filed: July 3, 2020
    Date of Patent: January 25, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Lucas Dvorozniak, Dominic J. Mongillo, Jr.