Patents Examined by Brian P Wolcott
  • Patent number: 10989070
    Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: April 27, 2021
    Assignee: General Electric Company
    Inventors: Brad Wilson VanTassel, Evan Andrew Sewall, Joseph Anthony Weber, Travis J Packer, Joseph Daniel Franzen, Jr., Bryan David Lewis
  • Patent number: 10989215
    Abstract: A compressor system includes a gas compressor with dry gas seals about a driveshaft. The compressor system also includes a fugitive gas system having a gas conduit in fluid communication with a collection cavity in a collector coupled to the gas compressor to receive fugitive gas leaked through a pressurized gas leakage path. The fugitive gas system may be structured for flaring the gas, and includes a pressure control system with an accumulator tank, and a vent line for venting gas pressure and having a backpressure regulator therein. Fugitive combustible gas is conveyed through a flow restriction orifice downstream of the compressor.
    Type: Grant
    Filed: September 5, 2017
    Date of Patent: April 27, 2021
    Assignee: Solar Turbines Incorporated
    Inventors: Donghui Zhang, Christopher Moffatt, Avneet Singh, Sean Garceau
  • 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: 10982683
    Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: November 25, 2014
    Date of Patent: April 20, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Lee Drozdenko, James O. Hansen, Jesse C. Meyer, Maria C. Kirejczyk, Scot A. Webb, Brandon A. Gates, Richard B. Bergethon
  • Patent number: 10975725
    Abstract: A turbofan including a low-pressure shaft; a high-pressure shaft; a fan shaft; a reducing mechanism that couples the low-pressure shaft to the fan shaft; and a maximum of six chambers that accommodate the bearings of the low-pressure shaft, the bearings of the high-pressure shaft and the bearings of the fan as well as the reducing mechanism.
    Type: Grant
    Filed: March 15, 2017
    Date of Patent: April 13, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Romain Guillaume Cuvillier, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Jeremy Dievart, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
  • Patent number: 10975883
    Abstract: A flow path includes a return bend portion which guides a working fluid to an inside in the radial direction by reversing the working fluid discharged to an outside in a radial direction from an upstream-side impeller, and a guiding flow path which is connected to a downstream side of the return bend portion and leads the working fluid to the inside in the radial direction so as to guide the working fluid to the downstream-side impeller. In a return vane which is provided in the guiding flow path, a trailing edge is formed such that a second end portion on a second side in an axial direction is positioned closer to an inside in a radial direction than a first end portion on a first side in the axial direction.
    Type: Grant
    Filed: February 20, 2018
    Date of Patent: April 13, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventor: Shuichi Yamashita
  • Patent number: 10968764
    Abstract: A turbine shroud assembly of a gas turbine engine includes seal segments made from ceramic matrix composite materials. The mounting assembly used to support the seal segments has heat shields adapted to resist radiant heating from the seal segments, especially portions of the seal adjacent to a primary gas path along the turbine shroud assembly.
    Type: Grant
    Filed: May 31, 2019
    Date of Patent: April 6, 2021
    Assignees: Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jeffrey M. Crutchfield, Anthony G. Razzell
  • Patent number: 10968752
    Abstract: A turbine airfoil includes an airfoil outer wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. At least one cooling passage is embedded in the airfoil outer wall and has a radially-elongated entrance manifold, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice. The radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold.
    Type: Grant
    Filed: April 2, 2019
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: James Tilsley Auxier, Tracy A. Propheter-Hinckley, Allan N. Arisi
  • Patent number: 10968828
    Abstract: An anti-icing system for a gas turbine system includes multiple nozzles arranged in a grid and configured to inject fluid within an air intake system of the gas turbine system upstream of a filter to keep ice from forming on the filter. Each nozzle of the multiple nozzles includes multiple orifices for injecting the fluid via jets. The anti-icing system also includes a nozzle head coupled to a nozzle of the multiple nozzles. The nozzle head is disposed over the multiple orifices and is configured to rotate relative to the nozzle. The nozzle head includes at least one outlet for injecting the fluid from the jets via at least one jet.
    Type: Grant
    Filed: March 6, 2019
    Date of Patent: April 6, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Laxmikant Merchant
  • Patent number: 10961867
    Abstract: A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. The means for removably mounting the power shaft include a pinion having a central bore, the shape of which is adapted to that of the power shaft in such a way that the pinion can slide over the power shaft; furthermore, the contour of the pinion is adapted to the shape of the gear of the first stage in such a way that the pinion can form a leading input pinion of the gearbox in said gear once the power shaft has been mounted in the reduction gearbox.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: March 30, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Olivier Lafargue, Sébastien Brotier, Alphonse Puerto
  • Patent number: 10954953
    Abstract: A gas turbine engine includes a rotor hub that extends along a longitudinal axis of the gas turbine engine and includes a radially outer surface that has a substantially axially extending projection and a substantially radially extending projection. A seal ring includes a body portion and at least one knife edge that extends outward from the body portion. A recess is in the body portion for accepting the axially extending portion of the rotor hub. A lock ring is in abutting contact with the seal ring and the radially extending projection on the rotor hub for securing the seal ring to the rotor hub.
    Type: Grant
    Filed: January 18, 2019
    Date of Patent: March 23, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: John E. Wilber
  • Patent number: 10947857
    Abstract: Labyrinth seal for a turbine engine, in particular of an aircraft, including a rotor element rotating about an axis of rotation, and a stator element extending around the rotor element The rotor element includes a series of annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. Each lip includes an inner peripheral body portion, an outer peripheral body portion and an upstream annular face for impact of an air flow during operation. At least one lip has, looking from the upstream annular face, a first annular cavity with a concave rounded cross-section on its inner peripheral body portion and a second annular cavity with a concave rounded cross-section on its outer peripheral body portion.
    Type: Grant
    Filed: September 24, 2018
    Date of Patent: March 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Jarossay, Guilhem Camille Francois Verron, Maurice Guy Judet, Clement Raphael Laroche, Guillaume Michel Maurice Giliberti
  • Patent number: 10941662
    Abstract: A mixed-flow turbine wheel is proposed which, compared to existing mixed-flow turbine wheels, has reduced mass and moment of inertia because radially-outer portions of existing mixed-flow turbine wheels are omitted. In a first possibility, the omitted material may be scalloping of the back face of the turbine wheel at a radial position outward of a base line which is a circle on the back surface of the wheel which indicates the minimum radius of the back surface. In a second possibility, part of the webbing of each blade is omitted to one side of the blade. Thus, viewing the turbine wheel in the axial direction, the area of the webbing outside the baseline and to one side of a radial line through the inducer tip, may be at least 20% less than that on the other side.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: March 9, 2021
    Assignee: Cummins Ltd.
    Inventors: Jon-Luke Keating, Jamie Archer
  • Patent number: 10941663
    Abstract: Airfoils for gas turbine engines are provided. The airfoils include a body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction. A first transitioning leading edge cavity is located adjacent one of the sides proximate the root of the body and transitions axially toward the leading edge as the first transitioning leading edge cavity extends radially toward the tip. A second transitioning leading edge cavity is adjacent the other side and adjacent the leading edge proximate the root of the body and transitions axially toward the trailing edge as the second transitioning leading edge cavity extends radially toward the tip. A portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the body.
    Type: Grant
    Filed: May 7, 2018
    Date of Patent: March 9, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley, Kyle C. Lana
  • Patent number: 10935040
    Abstract: A radial blade impeller for an industrial fan assembly may include a cylindrical impeller hub having a hub outer surface and a hub shaft bore, a plurality of impeller blade assemblies circumferentially spaced about the hub outer surface and extending outward from the hub outer surface. A first sprocket disposed on a first end of the impeller hub engages a lateral edge of each of the impeller blade assemblies and has a plurality of first sprocket teeth extending outward from a first sprocket outer edge. Each of the first sprocket teeth corresponds to one of the impeller blade assemblies and engages and is secured to the first lateral edge of the corresponding one of the impeller blade assemblies. A second sprocket disposed on a second end of the impeller hub has a similar configuration with second sprocket teeth aligning with and engaging opposite lateral edges of the impeller blade assemblies.
    Type: Grant
    Filed: June 19, 2017
    Date of Patent: March 2, 2021
    Assignee: The Boeing Company
    Inventor: Eric J. Johansen
  • Patent number: 10934849
    Abstract: Described are an airfoil array segment (100, 200, 300) having at least two airfoils (20, 30) and a platform (10) that features an axis asymmetrical platform surface (12). This platform surface features an elevation (110, 210, 310) that extends from the pressure side (21) of the first to the suction side (32) of the second airfoil (30). A highest point (111, 211, 311) of the elevation is more proximate to the suction side 32 of the second airfoil (30) than to the pressure side (21) of the first airfoil (20). Also described are an airfoil, a platform, an airfoil passage and a turbomachine.
    Type: Grant
    Filed: May 14, 2018
    Date of Patent: March 2, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Markus Brettschneider, Inga Mahle, Fadi Maatouk
  • Patent number: 10935044
    Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.
    Type: Grant
    Filed: August 1, 2019
    Date of Patent: March 2, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: Nathan Ottow, Johnathan Acker, Nate Cooper, Mark Whitlock, Michael Nesteroff
  • Patent number: 10927808
    Abstract: A wind control blade (31) of a wind guide (30) of the present invention forms a 20° wind control blade lateral curved surface gradient angle (32), a 30° wind control blade longitudinal spiral twist angle (33), a 180° wing control blade alignment angle (34), and a 15° wind control blade rear gradient angle (35). In addition, a turbine blade (41) forms a 30° turbine blade lateral curved surface gradient angle (42), a 40° turbine blade longitudinal spiral twist angle (43), and a 120° turbine blade alignment angle (44). The 20° wind control blade lateral curved surface gradient angle (32) and the 30° wind control blade longitudinal spiral twist angle (33) of the wind control blade (31) have more gradual and wider incidence angles than the 30° turbine blade lateral curved surface gradient angle (42) and the 40° turbine blade longitudinal spiral twist angle (43) of the turbine blade (41).
    Type: Grant
    Filed: November 26, 2015
    Date of Patent: February 23, 2021
    Inventor: Sang Kyu Sun
  • Patent number: 10927812
    Abstract: A method for operating a wind turbine includes operating, via a controller, the wind turbine according to a speed set point during normal operation of the wind turbine. The method also includes receiving, via the controller, a command to shut down the wind turbine or to curtail operation of the wind turbine. In response to receiving the command, the method includes initiating, via the controller, a shutdown procedure or a curtailment procedure of the wind turbine. During the shutdown procedure or the curtailment procedure of the wind turbine, the method includes dynamically adjusting a rate of change of the speed set point as a function of a speed tracking error, which corresponds to a difference between an actual rotor speed of the wind turbine and the speed set point.
    Type: Grant
    Filed: February 19, 2019
    Date of Patent: February 23, 2021
    Assignee: General Electric Company
    Inventor: Leonardo Cesar Kammer
  • Patent number: 10926851
    Abstract: The present invention relates to a lightweight composite propeller for an outboard motor, wherein the propeller has a separate hub and blades which are easily repaired when damaged, improves fuel efficiency because a lightweight composite material is used therefor, and is easily manufactured in large quantities.
    Type: Grant
    Filed: May 16, 2017
    Date of Patent: February 23, 2021
    Assignee: XINNOS CO., LTD.
    Inventors: Yang Ryul Choi, Tae In Cha, Jae Hoon Jung