Patents Examined by Richard Edgar
  • Patent number: 10690113
    Abstract: The present disclosure relates to a wind turbine blade. The wind turbine blade comprises a load carrying structure made of a fibre-reinforced polymer material. The load carrying structure comprises a plurality of stacked fibre layers or fibre mats in a thickness of the load carrying structure. The plurality of said stacked fibre layers or fibre mats are made of hybrid material comprising both carbon fibres and glass fibres and having a carbon fibre ratio. The carbon fibre ratio is defined as a volume of the carbon fibres divided by a total volume of the glass fibres and carbon fibres. At least a number of said stacked fibre layers or fibre mats have different carbon fibre ratios such that the carbon fibre ratio of fibre material varies through the thickness of the load carrying structure.
    Type: Grant
    Filed: December 19, 2016
    Date of Patent: June 23, 2020
    Assignee: LM WP PATENT HOLDING A/S
    Inventors: Lars Nielsen, Klavs Jespersen
  • Patent number: 10690115
    Abstract: There is provided a sliding component including, a first sliding part which is non-conductive and which has a sliding surface; and a conductive member provided in the first sliding part or provided on a side opposite to the sliding surface of the first sliding part.
    Type: Grant
    Filed: August 17, 2016
    Date of Patent: June 23, 2020
    Assignee: MINEBEA MITSUMI INC.
    Inventor: Tatsuhiko Murakami
  • Patent number: 10690148
    Abstract: A centrifugal compressor (20) comprises: a housing (26); an impeller (34) having an axial inlet (70) and a radial outlet (72); a diffuser (82); and a control ring (90) mounted for shifting between an inserted position and a retracted position. The control ring comprises means (150, 160, 162, 166) for absorbing pulsations.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: June 23, 2020
    Assignee: Carrier Corporation
    Inventor: Vishnu M. Sishtla
  • Patent number: 10683767
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: June 16, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Ludovic Pintat, Pierre Hervé Fernand Marche, Guillaume Jochen Scholl, Thomas Michel Julien Mervant, Renaud Gabriel Constant Royan
  • Patent number: 10677078
    Abstract: The gas turbine has a plurality of inlet guide vanes each having a blade having a leading edge, a trailing edge, a span extending along the leading edge, and pivot members at opposite ends of the leading edge, and being pivotally mounted across the radial-to-axial intake via the pivot members, the pivot axis extending axially across a radial portion of the radial-to-axial intake. The plurality of inlet guide vanes include a plurality of first inlet guide vanes, and a plurality of second inlet guide vanes, the second inlet guide vanes having a trailing edge recess differing from the corresponding portion of the first inlet guide vanes. During operation, when the inlet guide vanes are pivoted past a given angle toward the tangential orientation, a radial flow of gas is allowed through the trailing edge recesses to avoid or impede vortex whistle.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: June 9, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Man-Chun Tse, Sid-Ali Meslioui
  • Patent number: 10677089
    Abstract: A fan is mounted on a fan shaft which constitutes part of a mainline shaft assembly centered for rotation on an engine axis X-X of a gas turbine engine. When in operation, the fan rotates about the engine axis X-X. A stub-shaft is arranged radially outwardly and concentrically with the fan shaft and adjoins an upstream facing face of a bearing sleeve. A fan catcher arm extends from the stub-shaft through the bearing sleeve and joins a fan catcher ring arranged downstream of the bearing sleeve and having an upstream facing face arranged to abut against a downstream facing face of the bearing sleeve in the event of a fan blade-off. Immediately downstream of the fan catcher ring is formed a shaft end which is configured to couple with an axially adjacent end of a low pressure compressor shaft. Immediately downstream of the bearing sleeve is a shaft end configured to connect with a turbine shaft.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: June 9, 2020
    Assignee: Rolls-Royce PLC
    Inventors: Kieran P. Lucey, Stephen J. Bendall
  • Patent number: 10677159
    Abstract: A gas turbine engine includes a low pressure compressor, a high pressure compressor, a turbine, and a gearbox. The high pressure compressor includes a plurality of stages split into a forward portion and an aft portion. One or both of the forward portion and the aft portion of the high pressure compressor are driven by the turbine through a gearbox such that the forward portion and the aft portion may rotate at different speeds.
    Type: Grant
    Filed: October 27, 2017
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventor: Justin Paul Smith
  • Patent number: 10669985
    Abstract: Various fluid turbine systems and methods are described. The turbine can be a vertical axis wind turbine configured to generate power from wind energy. The turbine system can have a blade assembly. The blade assembly can have a plurality of blades rotatable about an axis. The turbine system can have a concentrator positionable upwind and in front of a return side of the blade assembly. The concentrator can define a convex surface facing the wind. The turbine system can also have a variable concentrator positionable upwind of a push side of the blade assembly. The variable concentrator can be adjustable between a first position and a second position, the variable concentrator being capable of deflecting more wind toward the turbine in the first position than in the second position.
    Type: Grant
    Filed: August 23, 2017
    Date of Patent: June 2, 2020
    Assignee: CALIFORNIA ENERGY & POWER
    Inventors: William DeRuyter, Michael Allawos, Peter L. Coye
  • Patent number: 10670038
    Abstract: Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P?) perpendicular to the axis of elongation and intersecting the platform, the dist
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: June 2, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, William Henri Joseph Riera, Guillaume Olivier Vartan Martin
  • Patent number: 10669878
    Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, 35% copper, 30.0-45.0% combined nickel, cobalt, and iron with combined iron and cobalt content at most one-third of the nickel content, 2.0-8.0% aluminum, and 5.0-15.0% chromium.
    Type: Grant
    Filed: March 22, 2017
    Date of Patent: June 2, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Xuan Liu, Christopher W. Strock
  • Patent number: 10669862
    Abstract: An airfoil includes a leading edge and an opposing trailing edge. The airfoil includes a pressure sidewall and an opposing suction sidewall. A leading edge cavity is defined between the pressure sidewall and the suction sidewall. The leading edge cavity has a first end opposite the leading edge and a second end defined at a rib. The airfoil includes at least one pin structure defined in the leading edge cavity between the first end and the second end. The at least one pin structure includes a main body and a first branch. The main body is coupled to the second end and extends toward the first end. The first branch extends from the main body toward the first end.
    Type: Grant
    Filed: July 13, 2018
    Date of Patent: June 2, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Luis Tapia, Jason Smoke
  • Patent number: 10669863
    Abstract: A blade for a turbomachine bladed wheel having N blades. At one end, the blade presents a platform that is formed integrally with an airfoil of the blade. Over a portion of the axial extent of the blade, a section through the platform wall on a plane perpendicular to the axis (X) of the wheel is constituted mainly by two first straight line segments arranged respectively on the two sides of the airfoil. Each of these segments forms an angle of 90°-180°/N relative to the radial direction on either side of the airfoil.
    Type: Grant
    Filed: December 12, 2014
    Date of Patent: June 2, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Sami Benichou, Christian Bariaud, Stéphanie Deflandre, Sébastien Digard Brou De Cuissart, Patrick Emilien Paul Emile Huchin
  • Patent number: 10670044
    Abstract: An axial impeller for a fan or blower includes a hub and a plurality of blades. The geometry of the blades is determined by a course of a blade leading angle and of a blade trailing angle of blade sections from a blade root at the hub to a blade tip opposite the blade root, i.e., according to the hub ratio. The blade leading angle is curved to the left according to the hub ratio and/or the blade trailing angle is curved to the right according to the hub ratio and the blade leading angle is 29°±3° near the blade root and 14°±3° near the blade tip and/or the blade trailing angle is 69°±3° near the blade root and 27°±3° near the blade tip.
    Type: Grant
    Filed: March 3, 2016
    Date of Patent: June 2, 2020
    Assignee: Voith Patent GmbH
    Inventors: Juergen Dossner, Martina Harsch
  • Patent number: 10669887
    Abstract: A coolable airfoil for a gas turbine engine includes a suction side wall that extends from a leading edge to a trailing edge. A pressure side wall is joined to the suction side wall at the leading edge and the trailing edge and spaced from the suction side wall to form a cavity therein that includes a cooling circuit with a plurality of serpentine cooling passages. A cooling air inlet passage receives cooling air from a plenum formed between an outer platform and an engine case and routes the received cooling air from the plenum to the cooling circuit. The coolable airfoil may also include a cooling air feed elbow that includes a metering input orifice that receives compressor first discharge air that provides the received compressor first discharge air to a feed elbow cavity and is redirected via a feed elbow outlet passage to the cooling circuit.
    Type: Grant
    Filed: February 15, 2018
    Date of Patent: June 2, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Thomas Allwood
  • Patent number: 10669011
    Abstract: The invention relates to a rotating front part of an aircraft turbomachine intake comprising bolts for attaching a cone tip to an internal support, each bolt comprising a rear end that is screwed into the support and a front end that receives a clamping nut, a rotation-prevention portion of non-circular cross section of each bolt engaging with a hole of corresponding cross section of a rotation-prevention ring. Also provided are extraction bolts, of which a rear end is screwed into the filling piece, each bolt passing through a cone tip flange. Finally, the invention is configured such that, after removal of the nuts, forward tension on the bolts allows the removal of an assembly comprising the tip and the filling piece, while keeping the bolts screwed to the support.
    Type: Grant
    Filed: May 9, 2017
    Date of Patent: June 2, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sylvie Judith Devaux, Pierre Yves Heinry, Olivier Richard Lefebvre
  • Patent number: 10661862
    Abstract: Disclosed is a floating wind turbine assembly, including a floating platform and a wind turbine arranged on top of the floating platform, the wind turbine having a mast with a mast axis, of which a lower end is connected to the floating platform, and a nacelle arranged on top of the mast, wherein the floating platform is connected to a seafloor with a plurality of tensioned mooring lines, wherein the mooring lines each include a mooring line axis extending in a longitudinal direction of the mooring line, wherein the mooring line axes intersect each other at a crossing position on the mast axis and at an elevation level at or above the nacelle, as well as a method for mooring such a floating wind turbine assembly.
    Type: Grant
    Filed: June 27, 2016
    Date of Patent: May 26, 2020
    Assignee: SINGLE BUOY MOORINGS INC.
    Inventors: Cecile Melis, Christian Raymond Bauduin, Francois Caille
  • Patent number: 10662802
    Abstract: This application provides a steam turbine. The steam turbine may include a number of controlled flow runners and a number of controlled flow guides. The controlled flow guides may include an upstream passage ratio (Wup/W) of 0.4 to 0.7.
    Type: Grant
    Filed: January 2, 2018
    Date of Patent: May 26, 2020
    Assignee: General Electric Company
    Inventor: Brian Robert Haller
  • Patent number: 10662780
    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A airfoil skin cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The airfoil skin cooling passage extends to a platform skin cooling passage arranged in the platform. The platform skin cooling passage resupplied by a backside of the platform.
    Type: Grant
    Filed: January 9, 2018
    Date of Patent: May 26, 2020
    Assignee: United Technologies Corporation
    Inventors: Nicholas M. LoRicco, Dominic J. Mongillo, Jr.
  • Patent number: 10662957
    Abstract: A vacuum pump has, in at least either a stator disc to be disposed or a rotating disc to be disposed, a Siegbahn type molecular pump portion in which a spiral-shaped groove with a ridge portion and a root portion is engraved (disposed), and is structured to ensure high conductance at a returning flow channel formed at the outer periphery (outside) of the Siegbahn type molecular pump portion. This structure is created by a communicating portion (a groove portion, a slit) formed on each rotating disc, or an oblique plate disposed on the stator disc and the communicating portion formed on the rotating disc. The “communicating portion,” “groove portion,” and “slit” are configured to have “concave” shapes, a concave portion is provided by engraving a groove radially inward from an outer diameter portion (toward a side of a shaft of the vacuum pump) in the rotating disc (or stator disc).
    Type: Grant
    Filed: October 29, 2014
    Date of Patent: May 26, 2020
    Assignee: Edwards Japan Limited
    Inventors: Manabu Nonaka, Takashi Kabasawa
  • Patent number: 10662810
    Abstract: Disclosed is a lubricant supply system, for a bearing damper in a bearing housing, the bearing housing in an engine bearing compartment of a gas turbine engine, the bearing compartment rotatably supporting an engine component, including a first interface, a second interface, a bearing supply conduit fluidly coupled to the second interface and extending from the first interface to the second interface, the bearing supply conduit supplying lubricant to the bearing housing, a damper supply conduit located within the bearing supply conduit, extending between the interfaces, the damper supply conduit supplying lubricant to the bearing damper, and fluid in the bearing supply conduit is capable of insulting fluid in the damper supply conduit 108 from heat transferred through the interfaces.
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: May 26, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas Bruce Avis, Michael Dreher, Erik R. Granstrand