Patents Examined by David E Sosnowski
  • Patent number: 10414487
    Abstract: An aircraft propeller blade including a streamlined structure constituted by at least one piece of fiber reinforcement obtained by three-dimensionally weaving yarns and densified by a matrix, together with a spar including an enlarged portion extending outside the fiber reinforcement and forming the root of the blade, and a shaping portion present in a housing arranged inside the fiber reinforcement. The fiber reinforcement includes a non-interlinked zone forming the housing inside the fiber reinforcement. The non-interlinked zone opens out into the bottom portion and into the rear edge of the fiber reinforcement so as to form an opening for inserting the shaping portion of the spar into the housing of the fiber reinforcement. The opening present in the rear edge of the fiber reinforcement extends over a height that is less than the height of the housing.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: September 17, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Adrien Laurenceau, Adrien Jacques Philippe Fabre, Matthieu Gimat
  • Patent number: 10415589
    Abstract: A pump housing made of plastic sections is provided. The housing includes a first casing that has a first side facing the region in which a pumped medium will flow, and a second casing that has a second side facing the environment. The pump housing's first casing and second casing are both dimensionally stable, with a space between the first casing and the second casing. A filler material such as a self-expanding foam may be provided in the space. The pump casings may be standardized components, and multiple casings may be assembled to form pump housings to suit a particular application.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: September 17, 2019
    Assignee: KSB Aktiengesellschaft
    Inventors: Alexander Boehm, Armin Gaiser, Sven Kilian, Karl-Heinz Koefler, Alexander Puetterich, Schramm Bernd, Andrea Seemann, Markus Steffens, Frank Anna
  • Patent number: 10408133
    Abstract: The described accessory drive system for a gas turbine engine includes a gearbox driving a plurality of accessories including a cabin air compressor to provide cabin air and an engine starter to start the gas turbine engine. An electrical power supply separate from a main electrical power supply of the gas turbine engine is electrically coupled to the accessories. A clutch selectively engages an output of the gas turbine engine to mechanically couple the output to the gearbox. The clutch operates between an electrical drive state where it disengages from the output and only the electrical power supply provides electrical power to the cabin air compressor and the engine starter, and a mechanical drive state where the clutch engages the output and the gearbox drives at least one of the accessories.
    Type: Grant
    Filed: October 3, 2014
    Date of Patent: September 10, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Wintgens, Jean Dubreuil
  • Patent number: 10408218
    Abstract: A fan with a housing defining an interior and a flow path therein and a valve assembly including a valve element disposed in the flow path and configured to rotate between an opened position and a closed position, wherein the valve element closes the flow path and a linkage assembly and a method of operating.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: September 10, 2019
    Assignee: GE Aviation Systems LLC
    Inventor: Sukeyuki Kobayashi
  • Patent number: 10399687
    Abstract: Methods and apparatus to vary an air intake of aircraft engines are disclosed. An example nacelle assembly includes a fan cowl and an inlet cowl movably coupled to the fan cowl. The inlet cowl defines a primary flow path and an auxiliary flow path of an intake of the aircraft engine. The inlet cowl moves relative to the fan cowl between an open position to allow airflow via an auxiliary flow path and a closed position to prevent airflow through the auxiliary flow path.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: September 3, 2019
    Assignee: The Boeing Company
    Inventors: Ronald Tatsuji Kawai, John T. Bonet
  • Patent number: 10400747
    Abstract: A rotor including blades rotating around a rotation axis (X), each blade being configured to transmit to the rotation axis, during a revolution of the rotor around the rotation axis, under the effect of the flow of a fluid, alternately a driving torque that rotates the rotor, and a resistant torque tending to go against the rotation of the rotor, each blade including in a region of an outer longitudinal edge of the blade, a flexible part configured to retract towards the inside of the rotor, when the blade transmits the resistant torque to the rotation axis of the rotor, and to switch to a position extended towards the outside of the rotor, during the rotor half-revolution following a maximum retraction position, when the blade transmits the driving torque to the rotation axis of the rotor, the flexible part being driven only under the effect of the flow of the fluid.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: September 3, 2019
    Assignees: UNIVERSITÉ D'AIX-MARSEILLE, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE
    Inventor: Stéphan Norbert Guignard
  • Patent number: 10392942
    Abstract: The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: August 27, 2019
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Jeremy Metternich, Gregory Vogel, Elena P. Pizano, Edwin J. Kawecki
  • Patent number: 10378370
    Abstract: A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Matthew Budnick, Conway Chuong, Jonathan Ariel Scott
  • Patent number: 10370994
    Abstract: An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: August 6, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Joseph P. Lamusga, Ted J. Freeman, Aaron D. Sippel
  • Patent number: 10371007
    Abstract: A gas turbine engine has a turbine driving a gear reduction. The gear reduction drives a fan drive shaft assembly to, in turn, drive a fan rotor at a reduced speed relative to the turbine. A generator generates current upon rotation of the fan drive assembly. The generator supplies electric current to an electric motor driven pump. The electric motor driven pump delivers lubricant to components within the gear reduction.
    Type: Grant
    Filed: October 16, 2014
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Brian P. Cigal, Christopher M. Valva
  • Patent number: 10370997
    Abstract: A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: August 6, 2019
    Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.
    Inventors: Daniel Kent Vetters, David J. Thomas, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • Patent number: 10364020
    Abstract: A pitch change mechanism for a bladed rotor includes a driving sleeve, a drive shaft, a first pitch-changing element, a second pitch-changing element, and a plurality of blade drive gears. The driving sleeve has, in axial sequence, a first helical connection portion and a second helical connection portion. The driving sleeve is positioned concentrically with and surrounding the drive shaft. The first pitch-changing element has a first end drivingly engaged with the first helical connection portion, and a first ring gear portion at a second opposite end, while the second pitch-changing element has a first end drivingly engaged with the second helical connection portion, and a second ring gear portion at a second opposite end. The plurality of blade drive gears are arranged in a circumferential array around a longitudinal axis of the drive shaft.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: July 30, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Philip A Curnock, Mario Di Martino
  • Patent number: 10364680
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.
    Type: Grant
    Filed: August 14, 2012
    Date of Patent: July 30, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Bret M. Teller, Mark F. Zelesky, Scott D. Lewis, Brandon W. Spangler, Ricardo Trindade
  • Patent number: 10364681
    Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: July 30, 2019
    Inventors: Matthew Lee Krumanaker, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
  • Patent number: 10364684
    Abstract: A structure for disrupting the flow of a fluid comprises and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.
    Type: Grant
    Filed: May 14, 2015
    Date of Patent: July 30, 2019
    Assignee: General Electric Company
    Inventors: Jason Randolph Allen, Robert David Briggs, Gulcharan Singh Brainch, Curtis Walton Stover
  • Patent number: 10364690
    Abstract: A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.
    Type: Grant
    Filed: January 28, 2014
    Date of Patent: July 30, 2019
    Assignee: United Technologies Corporation
    Inventors: Jorge I. Farah, Jonathan P. Burt, Thomas J. Praisner
  • Patent number: 10358935
    Abstract: A turbocharger comprising: a turbine wheel; a compressor wheel; a shaft member connecting the turbine wheel and the compressor wheel, the shaft member, turbine wheel, and compressor wheel being located along the same longitudinal axis; and a varying geometric technology system comprising a first guide ring member, a second guide ring member, a plurality of rotatable guide vane members positioned between the first and second guide ring members and in a substantially circular arrangement at a first radius from the longitudinal axis, and a plurality of spacer members also positioned between the first and second guide ring members, and located between the longitudinal axis and the circular arrangement of guide vane members.
    Type: Grant
    Filed: October 21, 2016
    Date of Patent: July 23, 2019
    Assignee: BorgWarner Inc.
    Inventors: Matthew King, John R. Zagone
  • Patent number: 10358927
    Abstract: A retainer that protrudes from an inner shroud of a vane to a radially inner side and extends in a circumferential direction is formed with an opening that passes through the retainer in an axial direction and defines a space through which air flows. A width of the opening in the circumferential direction is wider than a width of a vane body in the circumferential direction at a radially inner end of the vane body at a position of the retainer in the axial direction.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: July 23, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yoshifumi Okajima, Masamitsu Kuwabara
  • Patent number: 10358931
    Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: July 23, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Chaitanya Paruchuri, Philip Joseph, Jae-Wook Kim
  • Patent number: 10352238
    Abstract: Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more flexible spring flanges, one or more bayonet flanges, and one or more pilot flanges, each configured to engage a respective portion of the turbine machine.
    Type: Grant
    Filed: November 3, 2016
    Date of Patent: July 16, 2019
    Assignee: ROLLS-ROYCE CORPORATION
    Inventor: Matthew A. Scott