Patents Examined by Dwayne J. White
  • Compressor blade locking mechanism in disk with tangential groove
    Patent number: 10465699
    Abstract: A compressor blade locking device can include: a first support including a first locking groove; a second support including a second locking groove; an upper plate disposed in the first locking groove and the second locking groove; and a plurality of bolts passing through the upper plate and coupled with the first support and the second support. The compressor blade locking device can further include a center support interposed between the first support and the second support.
    Type: Grant
    Filed: January 26, 2017
    Date of Patent: November 5, 2019
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventors: Matthew Montgomery, Iurii Goroshchak, Joohwan Kwak, Andrii Ievdoshyn
  • Housing element for an intermediate turbine housing
    Patent number: 10465560
    Abstract: A housing element (12) for an intermediate turbine housing of a gas turbine, in particular an aircraft gas turbine; the housing element (12) being installable or installed in the intermediate turbine housing radially outwardly, in each case between a plurality of circumferentially spaced struts; the housing element (12) having a planar form and, relative to the radial outer side (16) thereof, a plurality of depressions (18c), is provided. On the radial inner side (32, 34) thereof, the housing element (12) has at least one recess (26) that is configured outside of the regions in which depressions (18c) are formed on the radial outer side (16).
    Type: Grant
    Filed: February 7, 2017
    Date of Patent: November 5, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Wolfgang Bickmeier, Petra Kufner
  • Device for adjusting a gap between the housing of an impeller and the impeller in a radial compressor and a turbomachine
    Patent number: 10465705
    Abstract: A device for adjusting a gap between the housing of an impeller and the impeller in a radial compressor of a turbomachine is provided. The device comprises at least one mechanical setting device by means of which the housing of the impeller can be axially adjusted in a targeted manner for the purpose of adjusting the gap, wherein the at least one setting device can be actuated via an adjusting ring, and a transmission of a force and/or a torsional moment from the adjusting ring can be effected via at least one adjustment lever device, in particular a thread lever, or a tilting lever.
    Type: Grant
    Filed: October 18, 2016
    Date of Patent: November 5, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Simon Schuldt, Knut Rosenau
  • Airfoil turn caps in gas turbine engines
    Patent number: 10465528
    Abstract: Turn caps for airfoils of gas turbine engines including cavity sidewalls, a first turn cap divider extending between the cavity sidewalls and defining a turning cavity between the first turn cap divider and the cavity sidewalls, and a second turn cap divider disposed radially inward within the turning cavity. A first turning path is defined between the first turn cap divider and the second turn cap divider and a second turning path is defined radially inward of the second turn cap divider and a merging chamber is formed in the turn cap wherein fluid flows through the first turning path and the second turning path are merged, the merging chamber, the first turning path, and the second turning path forming the turning cavity.
    Type: Grant
    Filed: February 7, 2017
    Date of Patent: November 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Dominic J. Mongillo, Jr.
  • Bottom abutment device for a rotorcraft rotor, a rotorcraft rotor, and a rotorcraft
    Patent number: 10464665
    Abstract: A bottom abutment device for a rotor having a plurality of lift assemblies. The bottom abutment device comprises at least one abutment track per lift assembly. The bottom abutment device comprises a plate with a ring and one branch per lift assembly. The bottom abutment device has a plurality of supports, each support fastenable to a rotary member of the rotor, each support extending in part in an opening in a branch, the supports giving the plate a restricted degree of freedom to move in translation, the supports giving the plate at least one restricted degree of freedom to move in rotation about the axis of symmetry.
    Type: Grant
    Filed: December 13, 2016
    Date of Patent: November 5, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Alain Eberhard, Fabien Massal
  • Transmission device of fan
    Patent number: 10458419
    Abstract: A transmission device of a fan is provided. A central axis and an eccentric position of the transmission device are connected with a spindle and a connecting rod, respectively. The spindle is connected with a motor through gears. A first casing and a second casing of the transmission device are pivotally connected to each other. An accommodation hole of the second casing is provided with an elastic member and a press member to engage with an engaging recess of the first casing, such that the fan can be swung. When the user applies a force to change the angle of the fan, the press member is pressed by two press portions of the first casing to disengage from the engaging recess, such that the second casing can be turned relative to the first casing to prevent gear slipping or gear jumping of the motor, the gears, and the spindle.
    Type: Grant
    Filed: March 1, 2017
    Date of Patent: October 29, 2019
    Assignee: AIR COOL INDUSTRIAL CO., LTD.
    Inventor: Cliff Wang
  • Airfoil with seal between endwall and airfoil section
    Patent number: 10458262
    Abstract: An airfoil includes an endwall section and an airfoil section that defines, at least in part, an airfoil profile. At least one of the airfoil section or the endwall section includes a seal cavity, and a seal is disposed in the seal cavity.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: October 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Vibration damper structure and fan thereof
    Patent number: 10458435
    Abstract: A vibration damper structure and a fan thereof. The vibration damper structure includes a support body, a fixing seat and an elastic member. The support body has a lower end. The fixing seat has a tubular section. The tubular section has a protrusion end corresponding to the lower end of the support body and a receiving space. The receiving space has a bottom section. The elastic member is disposed in the receiving space of the tubular section and positioned between the support body and the fixing seat. Two ends of the elastic member are respectively in contact with the lower end of the support body and the bottom section of the receiving space. The vibration damper structure is applied to the fan to greatly reduce the vibration of the fan in operation.
    Type: Grant
    Filed: January 8, 2017
    Date of Patent: October 29, 2019
    Assignee: ASIA VITAL COMPONENTS CO., LTD.
    Inventors: Bor-Haw Chang, Yu-Tzu Chen, Chung-Shu Wang
  • Centrifugal fan with axial-flow wind
    Patent number: 10458417
    Abstract: A centrifugal fan with axial-flow wind includes a centrifugal fan wheel and a cover shell. The centrifugal fan wheel has a rotating core structure and a plurality of centrifugal vanes arranged around the rotating core structure; a circular wind guide surface is disposed on an internal side of the cover shell and around the rotating core structure and covered onto the centrifugal vanes, such that the circular wind guide surface can change a centrifugal airflow at the external periphery of the centrifugal vane into an axial-flow airflow.
    Type: Grant
    Filed: September 5, 2012
    Date of Patent: October 29, 2019
    Assignee: DELTA ELECTRONICS, INC.
    Inventors: Shih-Kang Hsiung, Hung-Chi Chen, Meng-Yu Chen
  • Undercut on airfoil coversheet support member
    Patent number: 10450872
    Abstract: Methods of providing an undercut on a support member for a coversheet and coversheet support systems having undercuts are provided. A coversheet support system may include a spar. The spar may include a support member on an outer surface of the spar. The support member may extend outward from the outer surface of the spar. The support member may include an outer surface and an undercut. The undercut may be located in a portion of the support member between the outer surface of the spar and the outer surface of the support member. In addition, the coversheet support system may include a coversheet. The coversheet may be metallurgically bonded to the outer surface of the support member.
    Type: Grant
    Filed: November 8, 2016
    Date of Patent: October 22, 2019
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Eric Koenig, Charles A. Bulgrin, Mike Engle, Jeffrey F. Rhodes
  • Gas turbine cooling apparatus
    Patent number: 10450864
    Abstract: Disclosed herein is a cooling apparatus of a gas turbine including a compressor disk unit mounted in a gas turbine and provided with compressor cooling passages; the torque tube units provided in an adhering state to each other while being adjacent to the compressor disk unit and provided with a cooling air supply passage communicating with the compressor disk cooling passage; and a turbine disk unit provided with a turbine disk cooling passage communicating with the cooling air supply passage of the torque tube unit, in which the torque tube units are disposed between the compressor disk unit and the turbine disk unit and coupled therewith in an adhering state to each other along an axial direction of a rotation shaft mounted in the gas turbine and the cooling air supply passage is open in horizontal direction along the axial direction from an edge of the torque tube unit.
    Type: Grant
    Filed: October 14, 2016
    Date of Patent: October 22, 2019
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Kyung Kook Kim
  • Turbine casing, turbine, core for casting turbine casing, and method for producing turbine casing
    Patent number: 10443414
    Abstract: A turbine casing includes: a shroud of a cylindrical shape defining an operational flow path between the shroud and a hub of a turbine rotor; a scroll outer peripheral wall continuing from an end side of the shroud and extending along a circumferential direction of the shroud; and a partition wall disposed inside the scroll outer peripheral wall and dividing an inside of the scroll outer peripheral wall into a first scroll flow path and a second scroll flow path disposed adjacent to each other in an axial direction of the shroud. The shroud, the scroll outer peripheral wall, and the partition wall are formed integrally by casting. The partition wall has a widening section which partially increases a communication area between at least two of the first scroll flow path, the second scroll flow path, and the operational flow path, in the circumferential direction of the shroud.
    Type: Grant
    Filed: July 3, 2014
    Date of Patent: October 15, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Takao Yokoyama, Yoji Akiyama
  • Seal assembly for gas turbine engine components
    Patent number: 10443420
    Abstract: A gas turbine engine assembly includes adjacent components and a seal assembly. The seal assembly is configured to block gasses from passing through the interface of the adjacent components.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: October 15, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Daniel K. Vetters
  • Method for repairing a blade
    Patent number: 10428657
    Abstract: A method for repairing a blade in a gas turbine engine comprises the steps of: isolating the damage on the airfoil of the blade; forming a cut back in the shape of elongated “D” shaped recess with a pair of fillets, a depth and a longitudinal axis of the “D” shaped recess having a length along the leading or trailing edge of the airfoil; and the fillets having a respective radius.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: October 1, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Raman Warikoo, Krishna Prasad Balike
  • Vibration damper structure and series fan thereof
    Patent number: 10428839
    Abstract: A vibration damper structure and a series fan thereof. The vibration damper structure includes a first support body, a second support body and an elastic member. The first support body has a first upper end and a first lower end. The second support body has a second upper end and a second lower end. The elastic member is disposed between the first and second support bodies. The elastic member has a first support end in contact with the first lower end and a second support end in contact with the second lower end. The vibration damper structure is applied to the series fan to greatly reduce the vibration of the series fan in operation.
    Type: Grant
    Filed: January 8, 2017
    Date of Patent: October 1, 2019
    Assignee: ASIA VITAL COMPONENTS CO., LTD.
    Inventors: Bor-Haw Chang, Yu-Tzu Chen, Chung-Shu Wang
  • Method to pilot using flexible profile
    Patent number: 10422238
    Abstract: A gas turbine engine according to the present disclosure includes a first component, a second component coupled to the first component, and a pilot unit. The pilot unit provides means for maintaining a pilot-setting force between the first and second component to retain alignment of the first component with the second component.
    Type: Grant
    Filed: November 9, 2015
    Date of Patent: September 24, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Samuel J. Lacombe, Patrick E. Bailey
  • End wall configuration for gas turbine engine
    Patent number: 10415392
    Abstract: A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apart to define flow passages (46) therebetween for channeling gases in an axial direction. A trough (62) is defined between a pressure side ridge (48) and a suction side ridge (58) located forward of each pair of airfoils (34a, 34b). Each trough (62) has a direction of elongation aligned to direct flow into the flow passage (46) centrally between each pair of airfoils (34a, 34b).
    Type: Grant
    Filed: June 18, 2014
    Date of Patent: September 17, 2019
    Assignee: SIEMENS ENERGY, INC.
    Inventor: Andrew S. Lohaus
  • Core arrangement for turbine engine component
    Patent number: 10406596
    Abstract: A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.
    Type: Grant
    Filed: May 1, 2015
    Date of Patent: September 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew S. Gleiner, Bret M. Teller, James T. Auxier
  • Cooling structure for a turbine component
    Patent number: 10400608
    Abstract: A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween.
    Type: Grant
    Filed: November 23, 2016
    Date of Patent: September 3, 2019
    Assignee: General Electric Company
    Inventors: Jessica Elizabeth Coomer, Matthew Thomas Beyer, Stephen Molter, Aaron Ezekiel Smith
  • Mini-disk for gas turbine engine
    Patent number: 10400603
    Abstract: Mini-disks of gas turbine engines are provided having an axially extending portion extending axially with respect to an axis of the engine, the axially extending portion configured to engage with a hub arm of a compressor of the engine, a radially extending portion extends radially with respect to the axis, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine, an intermediate portion extending between the axially extending portion and the radially extending portion, and at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.
    Type: Grant
    Filed: June 23, 2016
    Date of Patent: September 3, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Raymond S. Hummel, Julian Partyka