Patents Examined by Igor Kershteyn
  • Patent number: 10385871
    Abstract: An apparatus and method of managing negative incidence in a compressor is provided. The apparatus includes a first row of stationary main vanes, and a second row of stationary auxiliary vanes extending radially inwardly from a stationary casing of the compressor proximate the leading edges of the main vanes. A flow channel is defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of main vanes.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, Jr., Aspi Rustom Wadia
  • Patent number: 10385764
    Abstract: A turbocharger includes a waste gate valve, a compressor with a turbine, a turbine housing which houses the turbine, a bypass channel with an opening cross-section, a bypass channel portion formed in the turbine housing, an actuator housing with a separate coolant channel, an electric motor arranged in the actuator housing, a transmission with an output shaft, the transmission being arranged in the actuator housing and being provided as a worm wheel gear unit, and a control body coupled to the output shaft of the transmission. The bypass channel bypasses the turbine. The actuator housing is removably secured to the turbine housing. The control body controls the opening cross-section of the bypass channel.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: August 20, 2019
    Assignee: PIERBURG GMBH
    Inventors: Martin Nowak, Michael-Thomas Benra, Sven Nigrin, Stephan Zielberg
  • Patent number: 10385721
    Abstract: The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot (20) that defines a substantially radial axis of rotation of the blade and which is connected by a lever (34) to control means (40a, 40b) extending about said axis. The invention is characterized in that said control means include first links (40a) supported by said pivots and second links (40b) extending between said first links, said first and second links extending substantially along a same circumference of said axis and being connected to one another and to actuation means (56).
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: August 20, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lilian Yann Dumas, Kamel Benderradji, Alain Marc Lucien Bromann, Suzanne Madeleine Coustillas
  • Patent number: 10385715
    Abstract: Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees.
    Type: Grant
    Filed: August 29, 2016
    Date of Patent: August 20, 2019
    Assignee: United Technologies Corporation
    Inventors: Joey Wong, Conway Chuong
  • Patent number: 10378385
    Abstract: A turbine ring assembly includes ring sectors made of ceramic matrix composite material forming a turbine ring, and a ring support structure having first and second annular flanges, each ring sector having tabs. The first tab includes an annular groove in which there is received an annular projection of the first flange. The second tab of each ring sector is connected to the ring support structure by a resilient retention element. The second tab includes an opening in which there is received a portion of a retention element secured to the second annular flange of the ring support structure. The retention element is made of a material having a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors.
    Type: Grant
    Filed: December 12, 2016
    Date of Patent: August 13, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thierry Tesson, Maxime Carlin, Jordan Caron
  • Patent number: 10376950
    Abstract: A blade has a blade, passage extending in a blade height direction, a platform passage formed inside a platform, and a communication passage leading from an outer surface of a shaft-mounted part through the platform passage to the blade passage. An inner surface defining an inflow passage portion of the platform passage includes a shaft-side inner surface that faces a gas path side. The shaft-side inner surface spreads in a direction having more of a component of a blade thickness direction than a component of the blade height direction. An inner surface defining the communication passage joins to the shaft-side inner surface.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: August 13, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Keita Takamura, Satoshi Hada, Hidekatsu Atsumi, Tomofumi Shintani
  • Patent number: 10378380
    Abstract: A system includes a shroud segment for use in a turbine and includes a body having a leading and trailing edge, first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side interfaces with a cavity having a cooling fluid. A first channel includes a first and second end portion. A second channel includes a third end portion and a fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The second end portion includes a first segmented channel with first metering feature and the third end portion includes a second segmented channel with second exit feature. The first and second exit features meter a flow of the cooling fluid within the first and second channels.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: August 13, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Marc Lionel Benjamin, Benjamin Paul Lacy, Luis Alfonso Gonzalez, Michael Scott Soden
  • Patent number: 10377478
    Abstract: The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades.
    Type: Grant
    Filed: January 20, 2016
    Date of Patent: August 13, 2019
    Assignee: FLIR UNMANNED AERIAL SYSTEMS AS
    Inventors: Petter Muren, Trygve Frederik Marton, Ivar Johnsrud, Päl Hagh Sandberg
  • Patent number: 10370087
    Abstract: A propeller device for aircraft, spacecraft or watercraft comprising two or more blades and a spinner. The blades are arranged on a hub so that they can be in a deployed or a retracted position. The spinner comprises first, second and third movable portions configured for allowing deploying or retracting the blades and for keeping the blades deployed or retracted.
    Type: Grant
    Filed: September 12, 2016
    Date of Patent: August 6, 2019
    Assignee: AIRBUS DEFENCE AND SPACE S.A.
    Inventors: Jesús López Ferrer, Eugenio Garrido Corralejo
  • Patent number: 10370985
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection locates the ceramic blade track relative to the metallic carrier.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: August 6, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Jeffrey A. Walston, Aaron D. Sippel, John A. Weaver, David J. Thomas
  • Patent number: 10370086
    Abstract: A blade for a turbine engine propeller, in particular a propfan engine, comprising a protruding part on the leading edge thereof, wherein said blade comprises means for controlling the position of the protruding part along the leading edge thereof.
    Type: Grant
    Filed: January 22, 2015
    Date of Patent: August 6, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Laurence Francine Vion, Rasika Fernando, Norman Bruno André Jodet
  • Patent number: 10371205
    Abstract: A tidal current energy generating device includes an outer frame (1), at least one inner frame (2), at least two hydro turbines (3), at least one center shaft (4), at least one generator (5), and at least three bearings (6). The at least one inner frame (2) is separably disposed in the outer frame (1). At least two hydro turbines (3) are located below a water surface and are disposed in one inner frame (2). At least two hydro turbines (3) are disposed coaxially and are vertical-axis hydro turbines. At least one center shaft (4) is disposed through the at least two hydro turbines (3), the axis direction of the center shaft is perpendicular to the horizontal plane, and the center shaft (4) rotates along with the rotating of the hydro turbines (3). The at least one generator (5) is located above the water surface and connected with one end of the center shaft (4). The at least three bearings are sleeved on the center shaft (4) and are located on two sides of and between the two hydro turbines (3), respectively.
    Type: Grant
    Filed: June 30, 2015
    Date of Patent: August 6, 2019
    Assignee: ZHEJIANG ZHOUSHAN LHD ENERGY DEVELOPMENT CO., LTD.
    Inventor: Dong Lin
  • Patent number: 10370974
    Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.
    Type: Grant
    Filed: August 26, 2015
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
  • Patent number: 10370996
    Abstract: Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where during a non-operational state of the engine a reference point of the shoe is substantially centered within a range of radial deflections of the reference point of the shoe over the operating range of the engine.
    Type: Grant
    Filed: August 23, 2016
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Ross Wilson, Conway Chuong, Dwayne K. Mecklenburg
  • Patent number: 10371008
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: August 6, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Jeffrey A. Walston, Jun Shi
  • Patent number: 10371056
    Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.
    Type: Grant
    Filed: December 10, 2015
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, William K. Ackermann
  • Patent number: 10364822
    Abstract: A fan blade is mounted on a shaft or arranged to vary in pitch via rotation about a pitching axis. The fan blade is mounted with a center of mass offset from the shaft or pitching axis. This offset reduces torque around the shaft or pitching axis.
    Type: Grant
    Filed: August 23, 2016
    Date of Patent: July 30, 2019
    Assignee: FLEXXAIRE INC
    Inventors: Jonathan E. McCallum, George Antoszko, Peter Knight
  • Patent number: 10367441
    Abstract: A modular, electricity generating apparatus comprises an elongate, central member comprising a first end and a second end; at least one foil disposed about the central member in fluid interacting relation thereto; the solar foil comprising an outer surface having photovoltaic properties; the first end and the second end dimensioned and configured to be connected to a connecting node; and, the elongate central member at least partially formed of an electrically conductive material and configured to conduct electricity from at least one of the connecting nodes to the other of the connecting nodes.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: July 30, 2019
    Inventor: Charles Martin Sieger
  • Patent number: 10364702
    Abstract: The invention proposes a de-icing splitter nose at the inlet of the low-pressure compressor of a double-flow turbine engine. The splitter nose comprises an annular separation surface with a circular leading edge, the surface being adapted to separate an upstream flow into a primary flow and a secondary flow. The nose further comprises an electric de-icing device with a heating element having a series of parallel, electric, heating strips. The strips are inserted between two strata of dielectric material and are able to prevent the formation of ice on the annular surface, as close as possible to the leading edge.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: July 30, 2019
    Assignee: Safran Aeroboosters SA
    Inventors: David Bouillon, Ghislain Herbaut
  • Patent number: 10364818
    Abstract: A centrifugal compressor includes a housing that accommodates a wheel. The housing includes an air intake space formed on an entrance side of the wheel; a flow passage to guide fluid compressed by the wheel to the outside of the housing; a return flow passage opened on each wall surface of the air intake space and the flow passage to circulate a part of the fluid in the flow passage to the air intake space without passing through the wheel; and an introduction portion provided in the air intake space, and having an inner peripheral surface that forms a flow passage to guide the fluid from the outside of the housing to the wheel. A downstream end of the inner peripheral surface in a flowing direction of the fluid is located radially inward of the wall surface of the housing.
    Type: Grant
    Filed: December 29, 2015
    Date of Patent: July 30, 2019
    Assignee: IHI Corporation
    Inventor: Tomokazu Murayama