Patents Examined by Igor Kershteyn
  • Patent number: 10731494
    Abstract: Various embodiments include gas turbine seals and methods of forming such seals for advanced gas path (AGP) heat transfer designed gas turbine engines. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component formed of a ceramic matrix composite and including a seal slot located in an end face, each seal slot having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and an overhanging seal assembly disposed in the seal slot. The overhanging seal assembly including an intersegment seal including a plurality of seal segments defining two vertical seal segments and a plurality of horizontal seal segments and a first overhanging positioner shim seal and a second overhanging positioner shim seal, each including an extended portion. The overhanging seal assembly disposed in the seal slot so as to provide position constrainment of the two vertical seal segments.
    Type: Grant
    Filed: October 20, 2016
    Date of Patent: August 4, 2020
    Assignee: General Electric Company
    Inventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Matthew Troy Hafner
  • Patent number: 10731656
    Abstract: A self-adjusting drum system for use with a pump or similar rotating machinery includes a balancing drum mounted on a central shaft for joint rotation therewith. The shaft extends along an axial direction and the balancing drum has an outer surface. A fixed, stationary structure surrounding the balancing drum is provided. The stationary structure has an inner surface arranged so as to face the outer surface of the balancing drum, and an annular gap is provided therebetween. A bush element is arranged in the annular gap so as to leave clearance with respect to the inner and/or outer surfaces. A fixing component is further provided for fixing the bush element to the stationary structure so as to lock the bush element against movement along the axial direction and allow it to freely move along a radial direction, inside the annular gap.
    Type: Grant
    Filed: June 5, 2018
    Date of Patent: August 4, 2020
    Assignee: XYLEM EUROPE GMBH
    Inventor: Gottfried Huber
  • Patent number: 10731478
    Abstract: A turbine blade having a base and an airfoil, the base including a root end. The airfoil including a skin extending from the base and defining a first edge, a second edge, having a tip end opposite from the root end. The turbine blade further including a base rib extending from the base and into the airfoil, a center divider extending from adjacent the first edge towards the second edge, a center rib disposed between the center divider and the second edge, extending from adjacent the center divider towards the tip end and extending from adjacent the center divider towards the root end, a tip center rib extending from adjacent the second edge towards the first edge, a tip rib extending from adjacent the tip center rib towards the base, a dividing rib and a first channel.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: August 4, 2020
    Assignee: Solar Turbines Incorporated
    Inventors: Hongzhou Xu, Kevin Liu, Michael D. Fox
  • Patent number: 10731668
    Abstract: A retainer arrangement for the support of a fan on a light module of a headlamp for a vehicle as well as a fan holder for the generation of such a retainer arrangement. The fan is fastened in a detachable manner to the fan holder. The fan holder has a hinged locking element that can be moved into an open position. The fan can be installed in the fan holder and removed from the fan holder, and can be moved in a locked position, in which the fan is firmly fastened to the fan holder.
    Type: Grant
    Filed: May 16, 2018
    Date of Patent: August 4, 2020
    Assignee: Hella GmbH & Co. KGaA
    Inventor: Sebastian Scholz
  • Patent number: 10731475
    Abstract: A gas turbine engine article includes a blade that has a platform, an airfoil, and a root. The platform has a gaspath side and a non-gaspath side. The airfoil extends radially from the gaspath side and defines a leading end and a trailing end. The root is configured to secure the blade. The root extends radially from the non-gaspath side of the platform. The root defines forward and aft axial faces, and a radial channel in the aft axial face. The radial channel leads to an inlet orifice in the root. A cooling passage extends in the root from the inlet orifice.
    Type: Grant
    Filed: April 20, 2018
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley
  • Patent number: 10724529
    Abstract: The present disclosure discloses an omnidirectional oscillating fan with a clamp, including: a base, a mounting part being disposed on a mounting surface of the base, a main fan unit, disposed on a side of a support surface of the base, and an oscillating main control assembly, disposed between the main fan unit and the base. A cross section, perpendicular to an extending direction, of the mounting part has a circular shape. The main fan unit has a columnar shape. The oscillating main control assembly includes: a first rotational assembly, partially disposed in the mounting part, and a second rotational assembly, having one end rotatably assembled to the main fan unit and the other end fixedly assembled to a rotating end of the first rotational assembly, and being capable of rotating synchronously with the first rotational assembly.
    Type: Grant
    Filed: July 3, 2018
    Date of Patent: July 28, 2020
    Assignee: SHENZHEN LUANSHENG ELECTRONIC TECHNOLOGY CO. LTD.
    Inventor: Yong Gan Lin
  • Patent number: 10724376
    Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.
    Type: Grant
    Filed: February 8, 2018
    Date of Patent: July 28, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Nicholas Joseph Kray, Nitesh Jain, Nagashiresha Gontla, Narendra Digamber Joshi, Paul Gerard Marsland, Wayne Allen Spence
  • Patent number: 10724503
    Abstract: A system for generating its own air currents to run electric turbines. The system includes: a vertical tower or support provided with a rotating disk at its upper end, up to four laterally extending arms connected to the disk, each arm carrying a wind turbine generator with rotating blades/rotors attached at its outer end, a planetary gear system having a central sun gear and motor associated with the rotating disk and a main controller system connected to the vertical tower base, wherein the main control system controlling the startup input source from a state power supply system and a solar system supply operating the central motor.
    Type: Grant
    Filed: November 26, 2017
    Date of Patent: July 28, 2020
    Inventor: Ahmad Abdallah Al-Jassem Al-Qanaei
  • Patent number: 10724537
    Abstract: The present disclosure relates to a blade structure and a fan and a generator having the same. In accordance with the present disclosure, there is the effect that can ultimately enhance efficiency of the generator by forming the sweep structure or the spline structure on the blade in the inflow direction side of fluid to reduce a low-speed region around the tip of the blade.
    Type: Grant
    Filed: May 16, 2018
    Date of Patent: July 28, 2020
    Assignee: Doosan Heavy Industries & Construction Co. LTD.
    Inventors: Dai Hyun Ahn, Sung Ha Kim, Sung Hoon Ha
  • Patent number: 10718227
    Abstract: A blade tip clearance control apparatus is disclosed. The apparatus includes a rotor, a hydraulic clearance control device, and a cylinder locking device. The rotor includes a thrust collar, a pair of thrust bearings axially supporting the thrust collar, and a plurality of radially extending blades. The hydraulic clearance control device includes a first hydraulic cylinder moving any one of the pair of thrust bearings in a forward axial direction and a second hydraulic cylinder moving the other thrust bearing in the reverse axial direction. The cylinder locking device includes a first locking device restricting a forward moving distance of the first hydraulic cylinder and a second locking device restricting a reverse moving distance of the second hydraulic cylinder.
    Type: Grant
    Filed: November 18, 2018
    Date of Patent: July 21, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Yeong Chun Kim
  • Patent number: 10718212
    Abstract: A rotor for a turbomachine, includes a plurality of axially adjacently arranged rotor segments which are each provided with a central opening, an individual tie rod extending through the openings of the rotor segments, and two holding devices which are arranged on axially opposing ends of the tie rod and hold the rotor segments together, the rotor segments forming at least two rotor segment groups between which at least one other holding device is arranged.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: July 21, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventors: Steffen Jahrmarcht, Kevin Miny
  • Patent number: 10717516
    Abstract: A support structure for a propulsor blade includes at least one sleeve configured to support a root portion of the propulsor blade, the at least one sleeve fixedly attached to a surface of the root portion. The support structure also includes a preloading component configured to apply a residual compressive force to the at least one sleeve and the root portion of the propulsor blade, the residual compressive force configured to maintain an attachment of the at least one sleeve to the root portion. The propulsor blade and root portion may incorporate composite structural materials. The support structure and/or the preloading component increases the high cycle fatigue strength and bending capacity of blade retention assemblies (including, e.g., composite-to-metal joints) when subjected to high cycle bending loads under reduced centrifugal load conditions, thereby making further reductions in the size and weight of blade retention assemblies feasible.
    Type: Grant
    Filed: April 10, 2018
    Date of Patent: July 21, 2020
    Assignee: ROTATING COMPOSITE TECHNOLOGIES, LLC
    Inventors: John A. Violette, Eric Stephen Loos
  • Patent number: 10710712
    Abstract: An afterbody for a rotor blade of a rotorcraft is unitarily formed of a single material of construction. The afterbody includes an upper surface disposed from a lower surface, a concave leading edge connected to the upper surface and the lower surface, and a trailing edge formed at an intersection of the upper surface with the lower surface.
    Type: Grant
    Filed: March 26, 2018
    Date of Patent: July 14, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Joel J. McIntyre, Michael Christopher Burnett
  • Patent number: 10711622
    Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.
    Type: Grant
    Filed: April 2, 2018
    Date of Patent: July 14, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Changsheng Guo, Christopher W. Strock
  • Patent number: 10711688
    Abstract: A variable flow rate valve mechanism includes: a valve body which opens and closes an opening; a stem which is rotatably supported by a housing while the valve body is connected to a first end thereof; a cylindrical bearing which is inserted through a through-hole of the housing and supports the stem to be rotatable about an axis line of the stem; a link member which is connected to a second end of the stem; and a spring mechanism which is disposed in a gap between the link member and an end of the bearing, on the side of the second end. An end of the bearing includes an inclined surface which contacts the spring mechanism and is inclined with respect to the axis line of the stem.
    Type: Grant
    Filed: October 5, 2016
    Date of Patent: July 14, 2020
    Assignee: IHI Corporation
    Inventor: Michihiko Tanigaki
  • Patent number: 10703454
    Abstract: The present invention relates to a propulsion unit nozzle for being arranged around a propeller in a propulsion unit, comprising: a load bearing core structure extending in a circumference of the propulsion unit nozzle; and a plurality of hydrodynamic elements mounted on and enclosing the core structure thereby defining the outer and the inner surfaces of the propulsion unit nozzle. The invention further relates to a propulsion unit for a vessel comprising a propulsion unit nozzle and to a method for the manufacture of a propulsion unit nozzle.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: July 7, 2020
    Assignee: Kongsberg Maritime CM AS
    Inventors: Rune Garen, Steinar Aasebø
  • Patent number: 10704411
    Abstract: A system for operating a turbo machine is generally provided, the system including a variable vane assembly including a first plurality of vanes coupled together by a first unison member and a second plurality of vanes coupled together by a second unison member. An actuation system is coupled to each of the first unison member and the second unison member and a solenoid actuator is coupled to the variable vane assembly and the actuation system.
    Type: Grant
    Filed: August 3, 2018
    Date of Patent: July 7, 2020
    Assignee: General Electric Company
    Inventor: Mark Joseph Mielke
  • Patent number: 10704419
    Abstract: Turbine distributor sector for an aircraft turbine engine, including an external annular platform sector and an internal annular platform sector, the sectors being coaxial and being connected together by blade assemblies including inner cavities cooled by gas circulation, the external platform sector including through openings of which radially internal ends open into the inner cavities, wherein the external platform sector includes inner ducts for supplying the cavities with gas, the ducts including air outlets opening into the openings and air inlets opening onto a portion of the external annular surface of the external platform sector.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: July 7, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Josserand Jacques Andre Bassery, Jean-Charles Marcel Bernard Coetard, Raphael Jean Philippe Dupeyre, Etienne Leon Francois, Ba-Phuc Tang
  • Patent number: 10704403
    Abstract: A wastegate sealing jig (13) includes a base (14) which is fixable to an exhaust portion (11) of a turbocharger (1), the base (14) including a wastegate valve (6), and a turbine hole (12) which discharges exhaust gas in a turbine chamber (4b), a protrusion (15) which is provided in the base (14) so as to extend toward the exhaust portion (11), a valve member (16) which is attached to a distal end of the protrusion (15). The wastegate (5) is closed by the valve member (16) by inserting the valve member (16) between the wastegate (5) and the wastegate valve (6) of the turbocharger (1) in a state in which the wastegate valve (6) is opened.
    Type: Grant
    Filed: November 5, 2018
    Date of Patent: July 7, 2020
    Assignee: HONDA MOTOR CO., LTD.
    Inventors: Yasuo Watanabe, Soichiro Takahashi, Tomoki Kiyooka
  • Patent number: 10704424
    Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.
    Type: Grant
    Filed: September 4, 2014
    Date of Patent: July 7, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven W. Burd, Christopher R. Brdar, Derk S. Philippona