Patents Examined by Richard A Edgar
  • Patent number: 9976425
    Abstract: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: May 22, 2018
    Assignee: General Electric Company
    Inventors: David Wayne Weber, Mehmet Suleyman Ciray, Jacob Charles Perry, II
  • Patent number: 9976438
    Abstract: A stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least one radial plane, as well as at least one stator vane adjusting ring which is connected to the respective stator vanes and rotatable in the circumferential direction by means of an actuating device, where the stator vane adjusting ring is braced on a centrally arranged casing in the radial direction by means of several spacers distributed about the circumference and mounted on the stator vane adjusting ring, characterized in that a bush on which the spacer is mounted is fastened to the stator vane adjusting ring for each spacer, the bush being made from a plastic material with a high thermal expansion coefficient.
    Type: Grant
    Filed: September 22, 2015
    Date of Patent: May 22, 2018
    Assignee: Rolls-Royce Detschland Ltd & Co KG
    Inventor: Thomas Klauke
  • Patent number: 9970415
    Abstract: A method and a system for managing loads on a wind turbine are provided. The computer-implemented method is implemented using a processor coupled to a memory device. The method includes determining a first moment of a wind load acting about a first axis of a rotor of the wind turbine, determining a second moment of a wind load acting about a second axis of a rotor of the wind turbine, and determining a resultant moment of the first moment and the second moment. The method also includes generating an error signal indicating a difference between the resultant moment and a predetermined moment level threshold signal and generating, by the processor, a first activation signal over a range of the generated error signal between a first zero activation signal level and a first full activation signal level.
    Type: Grant
    Filed: June 12, 2014
    Date of Patent: May 15, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Pranav Agarwal, Jigar Jayesh Shah
  • Patent number: 9970461
    Abstract: A compressor unit is disclosed comprising at least a first motor driving in rotation at least one impeller of a compression stage, having at the outlet of the impeller a diffuser designed to centrifugally channel the gases coming from the impeller, and having a centripetal return channel downstream of the diffuser. The return channel includes at least one movable blade portion that, when moved, can vary a tangential component of the speed of the gases coming from the return channel.
    Type: Grant
    Filed: January 13, 2014
    Date of Patent: May 15, 2018
    Assignee: Thermodyn SAS
    Inventors: Gilles Nawrocki, Pascal Gaudez
  • Patent number: 9970307
    Abstract: Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints.
    Type: Grant
    Filed: March 19, 2014
    Date of Patent: May 15, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Shezan Kanjiyani, Bradley Reed Tucker, Natalie Wali, Daniel Hicks, Bill Macelroy
  • Patent number: 9970320
    Abstract: An exhaust housing hub of a turbomachine, including a connecting wall and an inner channel wall, the connecting wall connecting the inner channel wall to inner attachment flanges, wherein a radial section of the connecting wall is curved and can be formed, as required, as a single component with the inner channel wall, the hub also including a series of ribs extending radially between the connecting wall and the inner channel wall.
    Type: Grant
    Filed: October 22, 2013
    Date of Patent: May 15, 2018
    Assignee: SNECMA
    Inventors: Mario Cesar De Sousa, Frederic Noel, Nicolas Pommier, Olivier Renon
  • Patent number: 9963977
    Abstract: Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: May 8, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, James D. Hill, Gopal Das
  • Patent number: 9963983
    Abstract: A turbocharger for an internal combustion engine having a housing, an impeller arranged in the housing interior having an impeller shaft and being mounted in a bearing block, and an intermediate element between the impeller and the bearing block. The housing includes at least one flow channel for feeding or discharging a fluid to or from the impeller, and the intermediate element includes a wall section that delimits a least a section of at least one of the flow channels.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: May 8, 2018
    Assignee: Bayerische Motoren Werke Aktiengesellschaft
    Inventor: Jan Velthuis
  • Patent number: 9964117
    Abstract: The present invention relates to a compressor blade of a gas turbine having an airfoil and a blade root, said blade root and airfoil being made in one piece from a fiber-composite material, as well as a leading edge protector made from a sheet metal material, characterized in that the airfoil is provided with a radial groove extending substantially over the entire length of the airfoil and that the leading edge protector is detachably clamped onto the airfoil and is fixed with a sheet metal flange in the radial groove of the airfoil.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: May 8, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Karl Schreiber, Werner Hufenbach, Albert Langkamp, Tino Wollmann
  • Patent number: 9963993
    Abstract: A turbine ring of a turbomachine is described, having a one-piece ring structure which has an outer ring which is continuous in the circumferential direction of the turbine ring and has a fastening section for fastening the turbine ring on a housing section of the turbomachine, an inner ring which is segmented in the circumferential direction and has a plurality of inner ring segments which are mutually displaceable in the circumferential direction for guiding the hot gas and has front sealing segments and rear sealing segments, as seen in the axial direction of the turbine ring, these sealing segments being spaced a distance apart from one another in the axial direction and extending between the inner ring and the outer ring, as well as a turbomachine having such a turbine ring.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: May 8, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Manfred Feldmann
  • Patent number: 9964120
    Abstract: A fan shroud for an air cycle machine includes a tubular body extending axially between a first end and a second end of the shroud along a center axis of the fan shroud. A flange extends radially outward from the tubular body of the shroud at the first end of the shroud. At least one mounting hole extends through the flange. A sight hole extends through the flange and is positioned radially inward from the at least one mounting hole relative the center axis.
    Type: Grant
    Filed: January 6, 2016
    Date of Patent: May 8, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Eric Chrabascz, Seth E. Rosen
  • Patent number: 9964116
    Abstract: The present invention relates to an inducer geometry which can optimize the behavior stability of cavitation in an inducer having a plurality of blades of the same geometry. In the inducer having a plurality of blades of the same geometry, a blade loading at a tip side in a front half of a blade is larger than that in a rear half of the blade; and when a blade angle from a circumferential direction of the inducer is expressed by ?b (degree) and a meridional distance is expressed by m (mm), an increase rate d?b/dm of the blade angle at the tip side is not less than 0.2 from a blade leading edge to a non-dimensional meridional location of 0.15, and the increase rate d?b/dm of the blade angle at a mid-span is not less than 0.25 from the blade leading edge to the non-dimensional meridional location of 0.15.
    Type: Grant
    Filed: January 17, 2013
    Date of Patent: May 8, 2018
    Assignee: EBARA CORPORATION
    Inventor: Hiroyoshi Watanabe
  • Patent number: 9963986
    Abstract: A coupling support member including a pair of divided pieces is placed between an end portion of a guide vane and an attachment flange, and the pair of divided pieces is joined to the vane end portion from both sides in the vane thickness direction. A linear protrusion is formed on one of joint surfaces of the vane end portion. A groove engaged with the linear protrusion is formed in one of respective joint surfaces of the pair of divided pieces. The vane end portion is fastened between the pair of divided pieces. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.
    Type: Grant
    Filed: February 1, 2013
    Date of Patent: May 8, 2018
    Assignee: IHI CORPORATION
    Inventors: Hiroyuki Yagi, Tadahiro Ishigure, Takaomi Inada, Takeshi Murooka, Hideo Morita, Tatsuhito Honda
  • Patent number: 9957972
    Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a main body extending between a leading edge and a trailing edge separated in a chordwise direction and extending between a tip and a root in a spanwise direction. The main body defines a suction side and a pressure side separated in a thickness direction and a plurality of channels extending inwardly from at least one of said suction and pressure sides. A composite cover is attached to the main body. The composite cover includes a plurality of stiffeners each received within one of the channels. A cover skin is adjacent the stiffeners, and an over-wrap surrounds the stiffeners and the cover skin.
    Type: Grant
    Filed: August 12, 2014
    Date of Patent: May 1, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Larry Foster
  • Patent number: 9957799
    Abstract: A ring has a ring body with a central portion surrounding an axis and extending to first and second opposing ends separated by a split. The central portion has a first axial thickness. At least one retaining feature is formed on the ring body, the at least one retaining feature having a second axial thickness greater than the first axial thickness. An assembly and a gas turbine engine are also disclosed.
    Type: Grant
    Filed: September 19, 2012
    Date of Patent: May 1, 2018
    Assignee: United Technologies Corporation
    Inventor: Jason Arnold
  • Patent number: 9957839
    Abstract: The invention relates to an outside ring of a rotary shaft bearing of a turbomachine, comprising a first guiding edge of at least one rolling element, the first guiding edge comprising an inside surface of the first guiding edge, an outside surface of the first guiding edge opposite the inside surface and at least one through-hole passing through the inside surface and the outside surface. Moreover, the inside surface of the first guiding edge forms a shoulder for guiding the rolling element, the through-hole defining a lubricant drainage orifice.
    Type: Grant
    Filed: January 8, 2014
    Date of Patent: May 1, 2018
    Assignee: SNECMA
    Inventors: Serge Louis Antunes, Arnaud Bessy
  • Patent number: 9957971
    Abstract: A method for preventing a fan from burning down includes steps of: using a central processing unit (CPU) to detect rotational speed of forward operation of a fan and defining as a highest backward rotational speed value; using the CPU to detect operation direction and rotational speed of backward operation of the fan; and using the CPU to activate the fan to operate forward or activate a rotation stop control signal to stop the fan when the fan impeller rotates forward or backward by return air, if the rotational speed of the rotation stop control signal is smaller or larger than the highest backward rotational speed value, the CPU activating the fan to operate forward or making the fan to generate a warning signal and keeping providing the rotation stop control signal. The method can prevent the fan from burning down and enhance the stability.
    Type: Grant
    Filed: April 28, 2015
    Date of Patent: May 1, 2018
    Assignee: ASIA VITAL COMPONENTS CO., LTD.
    Inventors: Qing-Wu Hu, Dong-Qi Tian, Bao-Lin Yao
  • Patent number: 9957900
    Abstract: One embodiment of the present discloses includes a system. The system includes a turbine and a fluid supply system. The turbine includes a main flow path, a plurality of turbine blades disposed along the main flow path, at least one flow control area disposed along the main flow path, and at least one fluid injection port fluidly coupled to the main flow path. The fluid supply system is fluidly coupled to the at least one fluid injection port, wherein the fluid supply system is configured to supply a fluid to the at least one fluid injection port to adjust an effective area of the at least one flow control area.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: May 1, 2018
    Assignee: General Electric Company
    Inventors: Mehdi Milani Baladi, Edward Michael Yanosik, Jr., Richard Bradford Hook, Jr., Scott Edward Farley, Gordon Jeffery Follin
  • Patent number: 9957964
    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: May 1, 2018
    Assignee: General Electric Company
    Inventors: Moorthi Subramaniyan, Jaya Rao Venkata Satya Vuppala
  • Patent number: 9951640
    Abstract: A structure providing compliance and sealing between ceramic or ceramic composite (CMC) part and a metallic part has an interface component for centering the CMC part in the metallic part, thus reducing thermal stress motion of the CMC component. In gas turbine engine applications, the structure comprises a CMC blade track inserted in a clip placed within a metallic hanger. The clip provides for radial compliance and secures controlled leakage of cooling air required to ensure that acceptable temperatures are maintained for the metallic structures. A washer is positioned adjacent to the clip provide for axial orientation of the blade track.
    Type: Grant
    Filed: December 27, 2013
    Date of Patent: April 24, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: William I. Westphal, Clayton C. Smith