Patents Examined by Dwayne J. White
  • Patent number: 9810087
    Abstract: A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a second condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: November 7, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Corcoran, Daniel A. Snyder
  • Patent number: 9810226
    Abstract: The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.
    Type: Grant
    Filed: June 14, 2013
    Date of Patent: November 7, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Marco Micheli, Wolfgang Kappis, Luis Federico Puerta
  • Patent number: 9810075
    Abstract: A damper seal received in a cavity of a turbine blade includes a central body with two ends and a two sides. A portion extends from each end, one side has a faceted edge, and a projection extends from the other side to receive a lug of the turbine blade to align the damper seal relative to the turbine blade.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: November 7, 2017
    Assignee: United Technologies Corporation
    Inventors: Kyle C. Lana, John E. Paul
  • Patent number: 9803621
    Abstract: The present invention relates to methods, apparatus and computer program products for controlling a wind turbine that comprises a nacelle and one or more turbine blades to reduce or prevent edgewise vibrations building up on the one or more turbine blades. It is identified 202 whether the nacelle is unable to yaw to an upwind position and initiating a corrective action 203 to prevent edgewise vibrations building up on the one or more turbine blades if the nacelle is unable to yaw to an upwind position.
    Type: Grant
    Filed: June 6, 2013
    Date of Patent: October 31, 2017
    Assignee: VESTAS WIND SYSTEMS A/S
    Inventors: Kenneth Tougaard Simonsen, Paw Rosenvard, David Steele
  • Patent number: 9803491
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.
    Type: Grant
    Filed: December 31, 2012
    Date of Patent: October 31, 2017
    Assignee: United Technologies Corporation
    Inventors: Brian Ellis Clouse, David F. Cloud, Donna Clough
  • Patent number: 9797261
    Abstract: A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: October 24, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian Tibbott, Peter Thomas Ireland, Anthony John Rawlinson, Irene Cresci
  • Patent number: 9797266
    Abstract: A closer for an attachment orifice of an OGV in a turbine engine, the vane having a blade fixed to a root provided with attachment orifices, the closer including a cup adapted to be fixed in the attachment orifice of an OGV; a cylindrical shaped plug engaging in the cup, the plug including an upper face inclined relative to the ground plane of the plug; a guide adapted to position the plug on the cup by rotation into a working position, in which the upper face of the plug coincides with the surface level of the vane root; a blocking system to block the plug in the working position.
    Type: Grant
    Filed: June 2, 2015
    Date of Patent: October 24, 2017
    Assignee: SNECMA
    Inventors: Kaëlig Merwen Orieux, Thierry Georges Paul Papin
  • Patent number: 9797262
    Abstract: A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.
    Type: Grant
    Filed: May 23, 2014
    Date of Patent: October 24, 2017
    Assignee: United Technologies Corporation
    Inventors: Carl S. Richardson, Mark J. Rogers, Jonathan J. Earl, Kenneth E. Carman, Richard K. Hayford
  • Patent number: 9797404
    Abstract: A ventilation assembly having a main housing that can be pre-installed in a wall or ceiling aperture. A fan assembly can be inserted through the aperture and releasably mounted within the main housing. The fan assembly can be removed from the main housing and replaced without removing the main housing from the wall or ceiling. An accessory component can be releasably mounted to the fan assembly either through the aperture when the fan assembly is mounted or prior to installation of the fan assembly.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: October 24, 2017
    Assignee: BROAN-NUTONE LLC
    Inventors: Daniel L. Karst, Benjamin Thorpe Puffer, Brent Elliott Coffey
  • Patent number: 9790806
    Abstract: One exemplary aspect of this disclosure relates to an assembly for a gas turbine engine having an engine axis. The assembly includes a case including an integrally formed projection configured to extend transverse to the engine axis. The assembly further includes an engine component including a flange configured for contact with the projection to limit motion of the component along the engine axis.
    Type: Grant
    Filed: June 5, 2015
    Date of Patent: October 17, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nathan F. Champion, Stephen H. Mattia
  • Patent number: 9790796
    Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.
    Type: Grant
    Filed: September 19, 2013
    Date of Patent: October 17, 2017
    Assignee: General Electric Company
    Inventors: John David Stampfli, Ajay Keshava Rao, Rudolf Konrad Selmeier
  • Patent number: 9784117
    Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes a blade outer air seal segment, a linkage, a rocker arm and an actuation device. The linkage is attached to the blade outer air seal segment. The rocker arm includes a first arm and a second arm engaged with the linkage. The actuation device is engaged with the first arm. The actuation device is configured to pivot the rocker arm and thereby radially move the blade outer air seal segment.
    Type: Grant
    Filed: June 4, 2015
    Date of Patent: October 10, 2017
    Assignee: United Technologies Corporation
    Inventors: Brian Duguay, Timothy M. Davis
  • Patent number: 9784133
    Abstract: A turbine frame for a turbine engine having an axial centerline, the turbine frame comprising an inner hub, an outer hub encircling the inner hub, a plurality of struts extending between the inner and outer hubs and having a maximum width portion relative to the axial centerline and an airfoil comprising at least first and second fairings mounted to the inner and outer hubs and encircling one of the struts.
    Type: Grant
    Filed: April 1, 2015
    Date of Patent: October 10, 2017
    Assignee: General Electric Company
    Inventors: Apostolos Pavlos Karafillis, Martin Wayne Frash, Schuyler Javier Ortega, Angelo Parisi
  • Patent number: 9777743
    Abstract: A centrifugal fan impeller structure includes a hub and a blade body set. The hub has an extension section. The blade body set has multiple blade bodies. The blade bodies outward extend from the extension section of the hub. Each two adjacent blade bodies define therebetween a flow way, an air outlet and an air inlet. The air outlet and the air inlet are respectively positioned at two ends of the flow way in communication with the flow way. The air outlets are arranged at unequal intervals so as to greatly reduce noise in operation.
    Type: Grant
    Filed: November 6, 2012
    Date of Patent: October 3, 2017
    Assignee: Asia Vital Components Co., Ltd.
    Inventors: Chih-Wei Yang, Sheng-Pei Lee
  • Patent number: 9777622
    Abstract: In an adjustable guide vane mechanism for a turbine, comprising a bearing ring with a plurality of guide vanes rotatably supported on the bearing ring by means of guide vane shafts provided with actuating levers which are engaged by a rotatable ring, the rotatable ring comprises axially spaced radial inner and outer sections with a radially inclined center section joining the spaced radial inner and outer sections, the radially inner section being rotatably supported and the radially outer section extending around the actuating levers and having recesses in which the actuating levers are received for pivoting the actuating levers and the guide vanes upon rotation of the rotatable ring.
    Type: Grant
    Filed: January 1, 2015
    Date of Patent: October 3, 2017
    Assignee: IHI CHARGING SYSTEMS INTERNATIONAL GMBH
    Inventor: Lorenz Jaenike
  • Patent number: 9777744
    Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: October 3, 2017
    Assignee: General Electric Company
    Inventors: Paul Griffin Deivernois, Jeremy Peter Latimer
  • Patent number: 9777578
    Abstract: An object is to provide a radial turbine blade that can reduce an impact loss of inflowing gas at a leading edge of the turbine blade and achieve a higher turbine efficiency, even in a case of a flow field corresponding to a low turbine operational velocity ratio U/C0 due to a throttling operation on a variable nozzle mechanism of a variable geometry turbocharger. In a radial turbine blade, a hub-side end portion Pa at a leading edge 51 of a turbine blade 50 is formed to be positioned more on a rear side in a rotation direction R of the turbine blade 50 than a shroud-side end portion Sc at the leading edge 51, and a straight line connecting between the shroud-side end portion Sc and the hub-side end portion Pa is inclined with respect to a straight line extending in a rotation axis direction from the shroud-side end portion Sc at the leading edge 51 onto a hub 17 surface by an angle in a range from 30° to 70° as viewed in the radial direction of the turbine blade 50.
    Type: Grant
    Filed: December 27, 2012
    Date of Patent: October 3, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Takao Yokoyama, Masaki Tojo, Satomi Nagae
  • Patent number: 9777742
    Abstract: A centrifugal fan impeller structure includes a hub having multiple blades. The blades extend from a circumference of the hub in a direction away from the hub. Each two adjacent blades define therebetween a flow way, an air outlet and an air inlet. The air outlet and the air inlet are respectively positioned at two ends of the flow way in communication with the flow way. The air outlets are arranged at unequal intervals so as to greatly reduce noise in operation.
    Type: Grant
    Filed: November 6, 2012
    Date of Patent: October 3, 2017
    Assignee: Asia Vital Components Co., Ltd.
    Inventors: Chih-Wei Yang, Sheng-Pei Lee
  • Patent number: 9776696
    Abstract: A propeller includes a bushing that rotates together with the propeller shaft, and a propeller damper disposed around the bushing, and an inner cylinder that surrounds the bushing via the propeller damper. The bushing includes a first cylindrical portion surrounding the propeller shaft, and a first protrusion protruding outward from the first cylindrical portion and integral with the first cylindrical portion. The inner cylinder includes a second cylindrical portion surrounding the bushing via the propeller damper and a second protrusion protruding inward from the second cylindrical portion. The inner cylinder is rotatable with respect to the bushing between a noncontact position and a contact position.
    Type: Grant
    Filed: April 13, 2015
    Date of Patent: October 3, 2017
    Assignee: YAMAHA HATSUDOKI KABUSHIKI KAISHA
    Inventor: Koma Ariga
  • Patent number: 9771870
    Abstract: A blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.
    Type: Grant
    Filed: March 2, 2015
    Date of Patent: September 26, 2017
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas D. Dierksmeier