Patents Examined by Alexander A White
  • Patent number: 10830215
    Abstract: A modular gas-heat anti-icing method as well as a device for high-power wind turbine blades, wherein a modular heating system is provided on the blade root, a ventilation duct is provided inside the blade, a wind deflector is provided at the end of the ventilation duct, which divides the front edge of the blade into two parts, so that the hot air in the ventilation duct is only to be conducted to the blade tip and then circulates into the blade root via the rear edge of the blade, enabling the hot air to circulate inside the blade and form a “blade root to blade tip to blade root” closed loop, so that the purpose of heating the front edge of the blade is achieved, and it is ensured that the whole blade does not ice by preventing the front edge of the blade from icing.
    Type: Grant
    Filed: March 18, 2015
    Date of Patent: November 10, 2020
    Assignee: ZHUZHOU TIMES NEW MATERIALS TECHNOLOGY CO., LTD.
    Inventors: Jiangang Zhao, Wentao Yang, Chaoyi Peng, Jingcheng Zeng, Binbin Hou, Jiaotong Jin, Xiao Li
  • Patent number: 10815790
    Abstract: An airfoil according to an example includes, among other things, a suction sidewall and a pressure sidewall. A tip wall extends from a leading edge to a trailing edge and joins respective outer ends of the suction and pressure sidewalls. A tip rib extends along a pressure side of the tip wall. A tip leakage control channel is provided at the tip wall and has a floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. Each of the tip leakage control vanes is contiguous with and extending from a suction side surface of the tip rib. The tip leakage channel extends toward the trailing edge while extending toward the suction sidewall. One or more of an internal cavity, a channel cooling aperture, and a sidewall microcircuit may be provided.
    Type: Grant
    Filed: March 12, 2018
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark F. Zelesky, Andrew S. Aggarwala
  • Patent number: 10815811
    Abstract: A rotatable component for a turbomachine and a method for regulating a circumferential ingress of a fluid at a trailing edge of the rotatable component are disclosed. The rotatable component includes an airfoil and a mechanical component. The airfoil includes a pressure side and a suction side. The mechanical component is coupled to the airfoil and includes a forward overhanging portion, and an aft overhanging portion. The forward overhanging portion is disposed at a leading edge of the airfoil and extends longitudinally beyond the leading edge. The aft overhanging portion is disposed at a trailing edge of the airfoil and extends longitudinally beyond the trailing edge, where both the forward and aft overhanging portions further extend circumferentially along the pressure side and the suction side of the airfoil. The aft overhanging portion includes a non-axisymmetric profile for regulating the circumferential ingress of the fluid from the pressure to suction sides.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Ganesh Seshadri, Mahendran Manoharan
  • Patent number: 10808548
    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. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher Whitfield, Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10801519
    Abstract: A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil.
    Type: Grant
    Filed: July 6, 2016
    Date of Patent: October 13, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ram Kulathu, Aldo Abate
  • Patent number: 10801309
    Abstract: A submersible fluid system for operating submersed in a body of water includes a fluid-end housing having an upper end and a lower end. A fluid rotor is disposed to rotate in the fluid-end housing and to receive and interact with a process fluid flowing from an inlet of the fluid-end housing to an outlet of the fluid-end housing. The fluid rotor is configured to thrust upwards toward the upper end when rotating. A bearing near the lower end of the fluid-end housing has an upward-facing bearing surface coupled to the fluid rotor and a downward-facing bearing surface coupled to the fluid housing, the bearing surfaces cooperate to support the upward thrust of the fluid rotor.
    Type: Grant
    Filed: September 12, 2012
    Date of Patent: October 13, 2020
    Assignee: FMC Technologies, Inc.
    Inventor: Christopher E. Cunningham
  • Patent number: 10794239
    Abstract: A rotary manifold for a rotor assembly of a cohesion-type drive includes a manifold body extending along a drive axis for rotation thereabout, a first ductwork internal the body for fluid communication with a plurality of first chambers of the drive, and a second ductwork internal the body for fluid communication with a plurality of second chambers of the drive. The second ductwork is in fluid isolation of the first ductwork.
    Type: Grant
    Filed: November 23, 2017
    Date of Patent: October 6, 2020
    Assignee: MCGUIRE AERO PROPULSION SOLUTIONS INC.
    Inventor: Daniel Matthew McGuire
  • Patent number: 10781697
    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 at an outer surface and a cold side wall at an inner surface. The skin passage extends a height in the radial direction, a width in a width direction, and a thickness in a thickness direction. The thickness is less than the width. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage at a core passage surface. 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.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: September 22, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher Whitfield, Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10774659
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall and including a tip rib extending chordwise along a pressure side of said tip wall. The tip wall includes a tip shelf disposed at a junction between said pressure sidewall and said tip rib. A tip leakage control channel at an outer surface of said tip wall, wherein said tip leakage control channel is between first and second tip leakage control vanes contiguous with a suction side surface of said tip rib, said tip leakage control channel extending toward said trailing edge while extending toward said suction sidewall. An air seal is radially outward of said tip wall and positioned to minimize leakage at said tip wall.
    Type: Grant
    Filed: March 12, 2018
    Date of Patent: September 15, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark F. Zelesky, Andrew S. Aggarwala
  • Patent number: 10731473
    Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.
    Type: Grant
    Filed: June 5, 2018
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel A. Snyder, Tracy A. Propheter-Hinckley, Dominic J. Mongillo
  • Patent number: 10718235
    Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of ceramic matrix composite material, each ring sector having a portion forming an annular base with an inside face defining the inside face of the turbine ring, and an outside face from which there extends a wall defining an internal housing in which a holder member made of metal material is present, the holder member being connected to the ring support structure and including a body from which elastically deformable holder elements extend inside the internal housing on either side of the body, the holder elements bearing against the wall.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: July 21, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Roussille, Thierry Tesson
  • Patent number: 10704401
    Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: July 7, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nicholas Aiello, James Cosby
  • Patent number: 10677169
    Abstract: The present disclosure relates to a geared turbofan engine.
    Type: Grant
    Filed: November 4, 2019
    Date of Patent: June 9, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Clive Breen
  • Patent number: 10605100
    Abstract: A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: March 31, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jacob John Kittleson, John McConnell Delvaux
  • Patent number: 10557475
    Abstract: In a rotor for a fluid pump which is made radially-compressible and expandable and has a hub (4) and at least one conveying element (10, 11, 19, 20) which has a plurality of struts (12, 13, 14, 15, 16, 21, 22, 27, 28) and at least one membrane (18) which can be spanned between them, provision is made for a design in accordance with the invention which is as simple and inexpensive as possible that at least one first group of struts is pivotable in a pivot plane, starting from a common base, and can thus be spanned open in the manner of a fan, wherein the conveying element lies along the hub and contacts it over its full length in the expanded state to avoid a pressure loss at the margin of the conveying element between it and the hub and thus to realize an optimum efficiency.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: February 11, 2020
    Assignee: ECP ENTWICKLUNGSGESELLSCHAFT MBH
    Inventor: Daniel Roehn
  • Patent number: 10557367
    Abstract: An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: February 11, 2020
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Richard K. Hayford, Christopher M. Jarochym
  • Patent number: 10550709
    Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.
    Type: Grant
    Filed: April 1, 2016
    Date of Patent: February 4, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Steven M. Hillier, Peter Broadhead, Joseph Doyle, Michael Jacquinto, Wesley Thibault, Jun Shi, Roderick Townes
  • Patent number: 10539032
    Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/?10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: January 21, 2020
    Assignee: General Electric Company
    Inventors: Sumeet Soni, Rohit Chouhan, Ross James Gustafson, Matthew Peter Scoffone
  • Patent number: 10519959
    Abstract: A compressor end head for providing a thermal barrier to a mechanical seal includes an inner end head having an inner end head opening, inner end head grooves in the inner end head opening, configured to place and seal an end portion of a compressor shaft; and an outer end head having an outer end head opening configured to enclose the inner end head.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: December 31, 2019
    Assignee: Nuovo Pignone Tecnologie Srl
    Inventors: Giusepe Sassanelli, Manuele Bigi, Suresh Devenbu
  • Patent number: 10502073
    Abstract: A rotor assembly is provided. The rotor assembly includes a plurality of blades spaced circumferentially. An airfoil of each blade includes a pressure side, a suction side, a pressure side nub extending from the pressure side, and a suction side nub extending from the suction side. An airfoil length is greater than one of (i) 40 inches, wherein the rotor is configured for operation at about 3600 rpm, and (ii) 48 inches, wherein the rotor is configured for operation at about 3000 rpm. The rotor assembly also includes a plurality of sleeves. Each of the sleeves extends from a first end to a second end. The first end is coupled to the pressure side nub of a first of the blades and the second end is coupled to the suction side nub of an adjacent second of the blades.
    Type: Grant
    Filed: March 9, 2017
    Date of Patent: December 10, 2019
    Assignee: General Electric Company
    Inventors: Robert Edward Deallenbach, John James Ligos, Kristopher John Frutschy