Patents Examined by Dwayne J. White
  • Patent number: 10801362
    Abstract: Centralizer apparatuses attached around a unison ring include rub buttons at inner ends of stud attached to and spaced apart from the unison ring and include rolling bearings. Each rolling bearing rotatably trapped within bearing chamber in bearing receptacle at inner end of stud. Tip cap includes bearing aperture trapping rolling bearing within bearing chamber. Rolling bearing extends partially through bearing aperture. Rolling bearing may be spring loaded within chamber by spring between the bearing receptacle and the rolling bearing. Stud may extend through and may be threaded into mounting aperture in unison ring and nut may be threaded onto outer end of stud. Variable stator vanes rotatably mounted to a casing and connected to vane crank arms connected to the unison ring mounted exterior to casing.
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: October 13, 2020
    Assignee: General Electric Company
    Inventors: Miguel Angel Hernandez, Socrates Aviles
  • Patent number: 10731481
    Abstract: A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.
    Type: Grant
    Filed: November 1, 2016
    Date of Patent: August 4, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Ted J. Freeman, James Glen Schwefel, Phil Bastnagel
  • Patent number: 10697319
    Abstract: A washing system is described for a gas turbine engine with an axial compressor, comprising: an inlet screen at the air flow inlet of the compressor to protect the compressor from foreign object damage, an arrangement of nozzles and manifolds for spraying the washing liquid, and a washing liquid supply system connected to the arrangement; the inlet screen comprises a supporting structure and a filtering net fixed to the supporting structure; the arrangement of nozzles and manifolds is integrated in the supporting structure of the inlet screen.
    Type: Grant
    Filed: October 30, 2014
    Date of Patent: June 30, 2020
    Assignee: Nuovo Pignone S.r.l.
    Inventors: Pierenzo Morriello, Gianfranco Pittella, Daniele Marcucci, Marco Frattallone
  • Patent number: 10684149
    Abstract: Vanes for use in gas turbine engines and methods of measuring cooling air flow through vanes are disclosed herein. Each vane includes an airfoil and an end wall. The airfoil is shaped to interact with hot gasses moving along a primary gas path during operation of the gas turbine engine. The end wall is coupled to the airfoil and shaped to define a boundary of the primary gas path near a radial end of the airfoil. The end wall includes a platform that is exposed to the primary gas path and a projection that extends away from the platform and is located outside the primary gas path.
    Type: Grant
    Filed: March 9, 2018
    Date of Patent: June 16, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Eric Koenig
  • Patent number: 10677259
    Abstract: A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil body. The metal leading edge further includes a second edge extending axially aftward from the nose along a suction side of the fan blade airfoil body. The first edge and the second edge forming a notch at the conjunction of the first edge, the second edge, and the nose. The metal leading edge also includes a nose length extending from a nose tip to the notch. The nose length at a first radial location is different from the nose length at a second radial location.
    Type: Grant
    Filed: May 6, 2016
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventors: Nitesh Jain, Vikulp Sharma, Nicholas Joseph Kray
  • Patent number: 10669857
    Abstract: A method for producing turbine rotor blades or the base bodies thereof includes a) providing the base body, which has, following one another along a longitudinal axis, a blade root, a blade platform and a blade airfoil, b) sensing a value of at least one parameter of the base body, at least one of the parameters representing a vibrational property of the base body, c) comparing the sensed value with a predetermined target interval, d) if the sensed value lies outside the target interval, reducing the mass of the base body, wherein the reduction of the mass takes place at the blade root and/or on the blade platform by introducing at least one recess and/or by reducing a dimension below the corresponding target value.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: June 2, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventors: Fathi Ahmad, Radan Radulovic
  • Patent number: 10670047
    Abstract: A centrifugal fan includes: an impeller configured to suction or discharge air; a motor configured to rotate the impeller; a housing configured to accommodate the impeller and have a suction port through which air is suctioned by rotation of the impeller and a discharge port through which air is discharged by rotation of the impeller; and a cut-off portion formed on one side of the discharge port. A flow cross-sectional area of air flowing in the housing is gradually increased from the cut-off portion to the discharge port in an air flow direction, and a distance from a lower portion of the impeller to an inner peripheral surface of the housing in a rotational axis direction of the impeller is gradually increased in at least a portion from the cut-off portion to the discharge port in the air flow direction.
    Type: Grant
    Filed: September 23, 2016
    Date of Patent: June 2, 2020
    Assignee: LG ELECTRONICS INC.
    Inventors: Kiwook Song, Jinsoo Kim, Dongwook Choi
  • Patent number: 10662803
    Abstract: An aerofoil body for a gas turbine engine is provided. The aerofoil body has leading and trailing edge portions, wherein one of the leading and trailing edge portions is a morphable edge portion having a composite layer structure. The aerofoil body further has a non-morphing central portion which forms pressure and suction surfaces of the aerofoil body between the leading and trailing edge portions. The composite layer structure includes a return spring, one or more shape memory alloy layers, and a flexible cover for the return spring and the one or more shape memory alloy layers. The flexible cover defines pressure and suction surfaces of the aerofoil body at the morphable edge portion. The one or more shape memory alloy layers are electrically heatable to deform the layers against the resistance of the return spring, and thereby alter the pitch of the aerofoil body at the morphable edge portion.
    Type: Grant
    Filed: March 14, 2017
    Date of Patent: May 26, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Matthew Mears
  • Patent number: 10661906
    Abstract: A housing for an air cycle machine includes a housing with a first end and a second end opposite the first end, a first duct adjacent the first end of the housing with an air inlet and an air outlet, a second duct adjacent the second end of the housing with an air inlet and an air outlet, and a collar in the housing extending into the second duct. The collar includes a first annular surface facing radially inward and configured to engage a journal bearing and a second annular surface facing radially inward and configured to engage a rotating shaft, wherein the second surface is monolithic with the housing.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: May 26, 2020
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Christopher McAuliffe, Brent J. Merritt
  • Patent number: 10662782
    Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes first and second airfoil pieces. The first airfoil piece defines a portion of the airfoil profile and has a first slot. The second airfoil piece defines a different portion of the airfoil profile and has a second slot. The first slot and the second slot together form a seal slot, and a seal is disposed in the seal slot.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: May 26, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10662794
    Abstract: Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include blade track segments. The blade track segments may include a cavity formed at a circumferential end of the blade track segment. The blade track segments may further include an assembly groove configured to provide a clearance for axial insertion of an inter-segment strip seal. An inter-segment strip seal may be axially inserted past the assembly grooves and into the cavity. The inter-segment strip seal may cover a gap between adjacent blade track segments, thus blocking hot, high pressure fluid from contacting the turbine casing.
    Type: Grant
    Filed: January 17, 2018
    Date of Patent: May 26, 2020
    Assignee: ROLLS-ROYCE CORPORATION
    Inventor: Sayon Das
  • Patent number: 10662799
    Abstract: A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.
    Type: Grant
    Filed: February 2, 2018
    Date of Patent: May 26, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Agnieszka M. Wusatowska-Sarnek
  • Patent number: 10662788
    Abstract: A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.
    Type: Grant
    Filed: March 14, 2018
    Date of Patent: May 26, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Agnieszka M. Wusatowska-Sarnek
  • Patent number: 10655479
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.
    Type: Grant
    Filed: July 11, 2018
    Date of Patent: May 19, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • Patent number: 10655637
    Abstract: A scroll casing forms a scroll flow passage of a centrifugal compressor, and, provided that, in a cross section of the scroll flow passage, Eo is an outer end of the scroll flow passage in a radial direction of the centrifugal compressor, Ef is a front end of the scroll flow passage in an axial direction of the centrifugal compressor, and Mw is a middle point of a maximum flow-passage width Wmax of the scroll flow passage in the radial direction, a flow passage height H of the scroll flow passage in the axial direction gradually increases from a position of the outer end Eo to a position of the front end Ef with respect to the radial direction, and the scroll flow passage has a recirculation flow suppressing cross section in which the front end Ef is disposed on an inner side, in the radial direction, of the middle point Mw, in a section disposed at least partially in a region closer to a scroll start than a connection position of the scroll start and a scroll end.
    Type: Grant
    Filed: October 29, 2015
    Date of Patent: May 19, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Kenichiro Iwakiri, Isao Tomita, Takashi Shiraishi
  • Patent number: 10655489
    Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.
    Type: Grant
    Filed: January 4, 2018
    Date of Patent: May 19, 2020
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Christopher Edward Wolfe, Victor John Morgan, Jason Ray Gregg
  • Patent number: 10655643
    Abstract: A cooling device includes a fan; an intake-side intrusion-preventing member that is provided on an intake side of the fan and prevents an object from entering the fan; an exhaust-side intrusion-preventing member that is provided on an exhaust side of the fan and prevents an object from entering the fan. The intake-side intrusion-preventing member and the exhaust-side intrusion-preventing member have different shapes.
    Type: Grant
    Filed: October 24, 2016
    Date of Patent: May 19, 2020
    Assignee: NEC Platforms, Ltd.
    Inventor: Tomoki Miwa
  • Patent number: 10655499
    Abstract: A preloaded ball bearing assembly includes a primary bearing assembly disposed between a rotating component and a static structure. The assembly also includes a preload bearing assembly disposed in contact with the rotating component. The assembly further includes a flexible support disposed between the primary bearing assembly and the preload bearing assembly.
    Type: Grant
    Filed: December 21, 2017
    Date of Patent: May 19, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Kevin Duffy, Ronnie K. Kovacik, Michael Gantt
  • Patent number: 10648456
    Abstract: The present disclosure is directed to a rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having a body shell with a pressure side, a suction side, a leading edge, and a trailing edge each extending between a root portion and a tip portion. Further, the rotor blade assembly includes a protection system configured to protect the rotor blade from ice accumulation or a lightning strike. The protection system includes at least one organic conductive element configured within the rotor blade. The protection system also includes a conductor source electrically or thermally coupled to the organic conductive element. Thus, the conductor source is configured to heat the organic conductive element so as to prevent ice from accumulating on the rotor blade or to provide a conductive path for the lightning strike.
    Type: Grant
    Filed: October 21, 2016
    Date of Patent: May 12, 2020
    Assignee: General Electric Company
    Inventors: Eric Michael Shain, Jignesh Patel, Richard Hardison, Amir Riahi
  • Patent number: 10648345
    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 core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin 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 core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. The resupply hole has a single inlet that is fluidly connected to multiple discrete outlet apertures.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: May 12, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Whitfield, Carey Clum, Dominic J. Mongillo, Jr.