Patents Examined by Nathaniel E Wiehe
  • Patent number: 10895273
    Abstract: A hydraulic lifting column comprising a base structure, a head structure and a lifting structure. The lifting structure comprising a hydraulic power unit and hydraulic linear actuators extending between the base structure and the head structure, the hydraulic power unit acting on the hydraulic linear actuators. The lifting structure comprising four linear actuator units with a mutually parallel, vertically oriented working direction. Each linear actuator unit comprising a double cylinder having two-cylinder bores arranged next to one another and two piston structures with piston rods oriented parallel to one another and extendable in opposite directions from the double cylinder. The four lower piston rods are connected to the base structure at the corners of a first quadrilateral and the four upper piston rods are connected to the head structure at the corners of a second quadrilateral.
    Type: Grant
    Filed: October 4, 2019
    Date of Patent: January 19, 2021
    Assignee: HAWE Altenstadt Holding GmbH
    Inventors: Martin Storz, Gerhard Rinninger, Erich Rankl, Thomas Stockmeier, Christian Hart, Danny Aurich
  • Patent number: 10890074
    Abstract: A gas turbine engine component includes an airfoil that has pressure and suction side walls that extend in a chord-wise direction between a leading edge and a trailing edge. The pressure and suction side walls extend in a radial direction between a platform and a tip to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction side walls and has a first passage along the pressure side wall and a second passage along the suction side wall. The first passage is configured to receive cooling air from a cooling air source. The second passage is configured to receive cooling air from the first passage near the tip. A platform passage is arranged in the platform and is configured to purge the cooling air from the second passage near the trailing edge.
    Type: Grant
    Filed: May 1, 2018
    Date of Patent: January 12, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy J. Jennings, Carey Clum
  • Patent number: 10883380
    Abstract: A gas turbine engine includes an airfoil and a deicing system. The airfoil radially extends from a hub towards a case disposed about a central longitudinal axis of the gas turbine engine. The deicing system includes an acoustic driver assembly arranged to apply acoustic energy to the airfoil to excite a predetermined vibratory mode of the airfoil.
    Type: Grant
    Filed: August 24, 2018
    Date of Patent: January 5, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Patent number: 10883508
    Abstract: A pump rotor includes a hub, a back plate and a plurality of blades extending from the hub and disposed on the back plate. Each of the plurality of blades has an outer surface essentially parallel to a rotational axis of the hub, and a first end adjacent the hub and a second end distal from the hub, the first end having a height from the planar surface that is less than a height from the planar surface of the second end. The plurality of blades is configured to cause a synchronized central column of flow.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: January 5, 2021
    Assignee: EDDY PUMP CORPORATION
    Inventors: Mugdha Shrikant Dokhale, Dan Wahlgren
  • Patent number: 10876416
    Abstract: There is disclosed a vane segment for a gas turbine engine. The vane segment includes vanes extending radially from inner ends to outer ends. The vanes have leading edges, trailing edges, and chords extending from the leading edges to the trailing edges. A platform circumferentially extends around the central axis. The platform has an inner face facing the central axis and an opposed outer face. The inner face of the platform is connected to the outer ends of the vanes. Ribs protrude away from the outer face and have lengths extending along the outer face.
    Type: Grant
    Filed: July 27, 2018
    Date of Patent: December 29, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jonathan Tebeka, Franco Di Paola, Jasrobin Grewal
  • Patent number: 10875639
    Abstract: A biplaner rotor blade has an upper airfoil section connected to a lower airfoil section such that the upper airfoil and lower airfoil are rotated in separate planes—an upper plane and a lower plane. The upper airfoil has a root end attached to a hub at an upper location of the hub and the lower airfoil has a root end attached to the hub at a lower location of the hub. The upper airfoil converges with the lower airfoil to form a blade tip end at the outermost portion of the blade, thus generating lift along two geometric planes.
    Type: Grant
    Filed: February 19, 2019
    Date of Patent: December 29, 2020
    Assignee: United States of America as represented by the Secretary of the Army
    Inventor: John P. Crocco
  • Patent number: 10876516
    Abstract: A fluid machine including a rotating shaft that extends parallel to a power generation shaft of a power generation unit, and that has an end coupled to the power generation shaft; a multiple rotors that are provided on the rotating shaft so as to be able to rotate in a circumferential direction of the rotating shaft, and that are arranged so as to be spaced in a rotational axis direction parallel to the axis of the rotating shaft; and a differential mechanism that is provided between a pair of rotors lying adjacent to each other in the rotational axis direction, and that combines the rotational force from each of the pair of rotors and transmits the rotational force to the rotating shaft.
    Type: Grant
    Filed: October 19, 2017
    Date of Patent: December 29, 2020
    Assignee: Japan Fudo Industry Inc.
    Inventor: Joshua Lawn
  • Patent number: 10876479
    Abstract: An acoustic liner can include a support layer having a set of partitioned cavities with open faces, a first facing sheet and second facing sheet both having perforations and operably coupled to the support layer such that the facing sheets overlie and close the open faces, and an aerogel layer operably coupled to the second facing sheet.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: December 29, 2020
    Assignee: MRA SYSTEMS, LLC.
    Inventors: Andrew Michael Roach, David Patrick Calder, Graham Frank Howarth
  • Patent number: 10876542
    Abstract: An axial flow fan includes a hub and a plurality of fan blade sets. The hub is configured to rotate around an axis. The fan blade sets are disposed at the peripheral of the hub, wherein each of the fan blade sets includes a first fan blade and a second fan blade arranged side by side along the axis and a flow channel is defined by each of the first fan blades and the corresponding second fan blade. Each of the flow channels has an inlet and an outlet opposite to each other, wherein at least one of each of the first fan blades and the corresponding second fan blade has a flow guiding hole and each of the flow guiding holes is located between the inlet and the outlet. Each of the flow guiding holes is communicated with the flow channel.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: December 29, 2020
    Assignee: Acer Incorporated
    Inventors: Kuang-Hua Lin, Cheng-Wen Hsieh, Wen-Neng Liao
  • Patent number: 10876429
    Abstract: An annular shroud assembly for a gas turbine engine is provided. The annular shroud assembly includes a plurality of first shroud segments having a same first arcuate length within a tolerance, at least one second shroud segment having a second arcuate length different than the first arcuate length and outside the tolerance, a plurality of first intersegment gaps between adjacent first segments, the first intersegment gaps having a circumferential dimension within a desired controlled range of dimensions, and at least two second intersegment gaps between opposed ends of the second segment and adjacent first segment. The first and second intersegment gaps are within the desired controlled range. Methods for controlling intersegment gaps between a plurality of shroud segments forming an annular shroud assembly and for forming such annular shroud assembly are also provided.
    Type: Grant
    Filed: March 21, 2019
    Date of Patent: December 29, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Daniel Lecuyer
  • Patent number: 10876421
    Abstract: There is provided a rotary machine including a rotary shaft configured to rotate around an axis; rotor blades; a casing surrounding the rotor blades radially outside the rotor blades, and in which a recessed portion accommodates tips of the rotor blades; a sealing portion extending from one of a bottom portion of the recessed portion and the tip of the rotor blade, and having a clearance with the other; and a variable breaker installed in the casing and is capable of being displaced between a protrusion position where the variable breaker protrudes into the recessed portion and an accommodation position where the variable breaker is accommodated in the casing.
    Type: Grant
    Filed: February 21, 2019
    Date of Patent: December 29, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Kazuyuki Matsumoto
  • Patent number: 10876420
    Abstract: A turbine blade retention system includes a turbine blade including a blade section and a blade platform on which the blade section is attached, the blade platform including a forward angel wing and an aft angel wing, the forward angel wing including a front blade seal groove, a disk configured to receive a plurality of the turbine blades, the disk including a front disk seal groove and an aft disk seal groove, a front seal plate, and an aft seal plate, wherein the front seal plate is slidably connectable to the turbine blade and the disk via the front blade seal groove and the front disk seal groove, and the aft seal plate is removably connectable to the turbine blade and the disk via the aft disk seal groove and a lower wall formed on the aft angel wing.
    Type: Grant
    Filed: September 14, 2017
    Date of Patent: December 29, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Ronald Rudolph
  • Patent number: 10871079
    Abstract: The invention relates to a sealing assembly for a turbine engine, comprising a wheel mounted inside a sectorised ring carrying an abradable material, having at an axial end an annular groove (14) in which a circumferential rail of the casing is engaged, sealing members being partly engaged in a recess (19) of a circumferential edge of a ring sector and another part thereof being engaged in a recess of a circumferential edge circumferentially opposite a circumferentially adjacent ring sector, characterised in that each sealing member comprises an axial end portion (180a) arranged radially between the circumferential rail and two adjacent ring sectors.
    Type: Grant
    Filed: September 21, 2018
    Date of Patent: December 22, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Daniel Delaporte, Anthony Pierre Beguin, Didier Noël Durand
  • Patent number: 10864985
    Abstract: A centrifugal force (CF) bearing for a rotorcraft rotor assembly includes an inner-member, an outer-member, and an elastic member interposed between the inner- and outer-members. The inner-member includes a boss configured for location to and engagement with a yoke. The boss includes a tapered profile (e.g., conic) portion. A tapered recess region of the yoke includes a profile that is substantially matched to receive and contact the tapered profile of the boss. The CF bearing is configured for attachment to a grip of the rotor assembly. The boss is configured to communicate mechanical loads (e.g., centrifugal force, lateral shear, vertical shear) from the grip to the yoke during operation of the rotor assembly.
    Type: Grant
    Filed: July 25, 2017
    Date of Patent: December 15, 2020
    Assignee: Textron Innovations Inc.
    Inventors: John McCullough, Mark Adam Wiinikka, Matthew Curtis Ledbetter
  • Patent number: 10865799
    Abstract: A centrifugal compression test device includes a flow path forming section and an inlet space forming section. The flow path forming section forms an introduction flow path, an inlet flow path, and an interstage inflow path. The introduction flow path guides a fluid from the outside toward the inside in the radial direction. The inlet flow path is connected to the introduction flow path. The interstage inflow path extends from the outside toward the inside in the radial direction and is connected to the inlet flow path. The inlet space forming section is formed an annular shape having an introduction opening section through which a fluid is introduced from a part in the circumferential direction and the outside in the radial direction at the first side of the introduction flow path. Further, a front end of the introduction flow path is connected to the inlet space forming section.
    Type: Grant
    Filed: March 15, 2017
    Date of Patent: December 15, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Shuichi Yamashita, Akihiro Nakaniwa, Masahiro Ishikawa, Yoshiaki Shoji
  • Patent number: 10859001
    Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft and output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft; and a gearbox support arranged to at least partially support the gearbox within the engine. A flight cycle ratio of: the ? ? torsional ? ? shear ? ? stress ? ? of ? ? the ? ? gearbox ? ? support ? ? at maximum ? ? takeoff ? ? conditions the ? ? torsional ? ? shear ? ? stress ? ? of ? ? the ? ? gearbox ? ? support ? ? at cruise ? ? conditions is less than or equal to 3.20. A method of operating the gas turbine engine is also disclosed.
    Type: Grant
    Filed: March 17, 2020
    Date of Patent: December 8, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Mark Spruce
  • Patent number: 10859268
    Abstract: The present disclosure is related to turbine vanes comprising ceramic matrix composite materials and vane ring assemblies including the same. The turbine vane may include mount extensions that extend outside a primary gas path to provide a point of coupling for attaching the turbine vane to a support structure.
    Type: Grant
    Filed: October 3, 2018
    Date of Patent: December 8, 2020
    Inventor: Michael J. Whittle
  • Patent number: 10858958
    Abstract: A turbine ring assembly includes a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a ring support structure secured to a turbine casing and having two annular flanges, each ring sector having two tabs held between the two annular flanges. The ring support structure includes an annular retention band mounted on the turbine casing, the annular retention band including an annular web forming one of the flanges. The two annular flanges exert stress on the tabs of the ring sectors. One of the flanges is elastically deformable in the axial direction of the turbine ring. The band has a first series of teeth distributed circumferentially on the band and the turbine casing has a second series of teeth distributed circumferentially on the casing, and the teeth of the first series and the teeth of the second series together provide circumferential jaw coupling.
    Type: Grant
    Filed: May 18, 2016
    Date of Patent: December 8, 2020
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel
  • Patent number: 10859096
    Abstract: A compressor diffuser for a gas turbine engine includes a plurality of diffuser passages including a first portion having a radial component, a second portion having an axial component, and a curved portion fluidly connecting the first portion and the second portion. The diffuser passages having a throat located within the first portion thereof, and including a first subset of passages and a second subset of passages. The throats of the first subset of passages have a first throat area that is different than a throat area of the throats of the second subset of passages.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: December 8, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Martin Drolet, Jason Nichols
  • Patent number: 10851654
    Abstract: An arrangement for a turbine has a metallic support structure having at least one radial support strut and a multiplicity of plate-shaped, fiber-reinforced ceramic segments which are arranged one on top of the other on the support structure and together define the circumferential contour, the segments being provided with through-openings through which the at least one support strut extends, wherein the at least one support strut has outwardly-extending projections that extend perpendicular to the radial direction and engage in corresponding recesses formed in the segments.
    Type: Grant
    Filed: June 2, 2016
    Date of Patent: December 1, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventor: Bernd Burbaum