Patents Examined by Andrew H Nguyen
  • Patent number: 10731603
    Abstract: A nacelle for a turbofan including a mobile cowl mobile in translation between a closing position and an opening position, a window on the upstream side by a fixed cowl and on the downstream side by the mobile cowl, and a reverser flap in rotation between a closed position and an open position. The nacelle includes a locking system with a groove fixed to the mobile cowl and extending between a first end and a second end, and a guided element mounted guided in the slide and fixed to the reverser flap, the guided element moving from the second end towards the first end with cowl movement and leaving the groove when the reverser flap begins rotation, and the guided element moving outside the groove while the reverser flap pivots from the positions and entering the groove at the end of rotation of the reverser flap.
    Type: Grant
    Filed: March 21, 2018
    Date of Patent: August 4, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Nicolas Jolivet
  • Patent number: 10724474
    Abstract: A thrust reverser for a gas turbine engine may comprise a frame, a first reverser door pivotally mounted to the frame at a first pivot point, a second reverser door pivotally mounted to the frame at a second pivot point, a first nacelle defining a first trailing edge of the gas turbine engine coupled between the frame and the first reverser door, and a second nacelle defining a second trailing edge of the gas turbine engine coupled between the frame and the second reverser door. The first nacelle and the second nacelle translate in an aft and radial outward direction relative to the gas turbine engine in response to the thrust reverser moving to a deployed position.
    Type: Grant
    Filed: May 1, 2018
    Date of Patent: July 28, 2020
    Assignee: ROHR, INC.
    Inventor: Timothy Gormley
  • Patent number: 10724475
    Abstract: Systems and methods are provided for a thrust reverser system with a straight vane thrust reverser cascade. The thrust reverser system may also include a blocker door and a turning door. The blocker door may divert air flowing within a bypass flow path of the aircraft propulsor to flow through the thrust reverser cascade. The turning door may then deflect air flowing from the thrust reverser cascade to provide reverse thrust. The straight vane thrust reverser cascade may allow for increased reverse thrust and/or a smaller, more efficient, aircraft propulsor.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: July 28, 2020
    Assignee: THE BOEING COMPANy
    Inventors: Chen Chuck, Zachariah B. VanDeMark
  • Patent number: 10718293
    Abstract: An actuator operable to drive a thrust reverser in a gas turbine engine, wherein the thrust reverser comprises first and second translatable sleeves. The actuator comprises a first actuating member moveable so as to translate the first sleeve and a second actuating member moveable so as to translate the second sleeve. The actuator further comprises an interlock arrangement operable in a locked mode in which the first actuating member and second actuating member are locked so as to move together and in an unlocked mode in which at least one of the first actuating member and second actuator member is free to move independently of the other. Operation of the actuator to open or close the thrust reverser comprises a first mode wherein the interlock arrangement is in the locked mode and a second mode wherein the interlock arrangement is in the unlocked mode.
    Type: Grant
    Filed: April 6, 2017
    Date of Patent: July 21, 2020
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventor: Stephen Davies
  • Patent number: 10718520
    Abstract: The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: July 21, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Mirko Ruben Bothien, Jaan Hellat, Bruno Schuermans
  • Patent number: 10718265
    Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor comprising a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor comprising a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: July 21, 2020
    Assignee: General Electric Company
    Inventors: Alan Roy Stuart, Jeffrey Donald Clements, Richard Schmidt, Thomas Ory Moniz
  • Patent number: 10711701
    Abstract: A starter air valve comprising a housing comprising an inlet at a first end and an outlet at a second end opposite the first end, the inlet being fluidly connected to the outlet through a fluid pathway; a valve injected into the fluid pathway dividing the fluid pathway into a first chamber and second chamber, the valve in operation adjusts fluid flow through fluid pathway; an actuator operably connected to the valve; a solenoid in variable electrical connection with the actuator; and a rotary spool valve fluidly connected to the first chamber, the rotary spool valve operable to rotate to at least one of a normal start position, a full manual override position, and a plurality of partial manual override positions, wherein the rotary spool valve is in variable fluid connection with the actuator, wherein the solenoid is in variable electrical connection with the actuator through the rotary spool valve.
    Type: Grant
    Filed: June 6, 2017
    Date of Patent: July 14, 2020
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventors: Leo J. Veilleux, Jr., Boris N. Grigorov
  • Patent number: 10704495
    Abstract: A pre-exit thrust reverser includes an upper reverser door pivotally mounted to a frame and having an upper trailing edge, a lower reverser door pivotally mounted to the frame and having a lower trailing edge and an exhaust duct fixedly mounted to the frame. The upper trailing edge is configured to extend aft of the lower trailing edge when the thrust reverser assumes a deployed state.
    Type: Grant
    Filed: November 27, 2017
    Date of Patent: July 7, 2020
    Assignee: ROHR, INC.
    Inventor: Martin Channell
  • Patent number: 10704497
    Abstract: The subject matter of this specification can be embodied in, among other things, a turbofan engine assembly includes a engine, a nacelle defining a generally forward-to-aft bypass air flow path, a thrust reverser comprising a first movable element, movable to and from a reversing position where at least a portion of the bypass air flow is reversed, a hydraulic actuator coupled to the first movable element to move the first movable element into and out of the reversing position, and a second moveable element, configured to move in synchronicity with the first moveable element, a first hydraulic valve operable to control a flow of hydraulic fluid for actuation of the hydraulic actuator, a second hydraulic valve operably coupled to the second moveable element and moveable between a restricted condition wherein the flow of hydraulic fluid is restricted, and a permit condition wherein the flow of hydraulic fluid is permitted.
    Type: Grant
    Filed: January 10, 2018
    Date of Patent: July 7, 2020
    Assignee: Woodward, Inc.
    Inventor: Joseph Thomas Kopecek
  • Patent number: 10697396
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure, a thrust reverser and a fan cowl. The thrust reverser includes a forward portion and a translating sleeve. The fan cowl is axially between the nacelle inlet structure and the translating sleeve. The fan cowl axially covers the forward portion of the thrust reverser. The fan cowl is axially structurally tied to the nacelle inlet structure. The fan cowl is radially and circumferentially structurally tied to the forward portion of the thrust reverser.
    Type: Grant
    Filed: October 17, 2017
    Date of Patent: June 30, 2020
    Assignee: Rohr, Inc.
    Inventors: Pablo T. Sanz Martinez, Jihad Ramlaoui
  • Patent number: 10690348
    Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attacked to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
    Type: Grant
    Filed: November 4, 2014
    Date of Patent: June 23, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Dennis M. Moura, Monica Pacheco-Tougas, Jonathan J. Eastwood, Lee E. Bouldin
  • Patent number: 10690088
    Abstract: A turbofan including a motor with a fan casing and a nacelle which includes a mobile cowl and a main slider bearing gratings and being mobile in translation between an advanced position and a retracted position in which the mobile cowl and the fan casing define, between them, a window. The nacelle also includes reverser flaps, each one being mounted articulated on the main slider between a closed position in which it obstructs the window and an open position in which it does not obstruct the window, a secondary slider mounted mobile in translation on the main slider between a first position and a second position, a transmission system configured to make each reverser flap pass from the closed position to the open position when the secondary slider passes from the first position to the second position, and a set of actuators that bring about a movement in translation of the main slider, and of the secondary slider.
    Type: Grant
    Filed: March 20, 2018
    Date of Patent: June 23, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Frédéric Ridray, Lionel Czapla, Frédéric Piard
  • Patent number: 10677194
    Abstract: There is provided an actuator for use in a thrust reverser of an aircraft, comprising a screw shaft and a nut translatable along the shaft between a retracted position and an extended position, a tine component comprising tine fingers formed with projections that are configured to engage formations on the nut when the nut occupies its retracted position to secure the nut against axial movement, and a movable lock member engageable with the tine fingers to restrict radial movement of the tine fingers in a first position, the lock member movable between the first position and a second position in which the lock member does not restrict radial movement of the tine fingers. The lock member is movable between the first position and the second position by means of an electromagnetic actuator.
    Type: Grant
    Filed: August 4, 2017
    Date of Patent: June 9, 2020
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventors: Andrew Hawksworth, Anthony Morgan
  • Patent number: 10677193
    Abstract: The present disclosure relates to the field of aircraft nacelles and concerns thrust reverser devices. More particularly, the present disclosure concerns a rear frame for a thrust reverser structure with a cascade vane of an aircraft nacelle, the nacelle comprising at least two longitudinal beams. The rear frame is intended to be attached to the two beams and to hold in place one or more cascade vanes in cooperation with a front frame. The rear frame comprises a common section having a substantially headband-like shape.
    Type: Grant
    Filed: January 4, 2017
    Date of Patent: June 9, 2020
    Assignee: SAFRAN NACELLES
    Inventors: Laurent Dubois, Laurent Ferrocino, Kamal Hafidi
  • Patent number: 10662895
    Abstract: A fan nacelle for an aircraft gas turbine engine. The nacelle includes an aft nacelle portion including a radially outer surface and a radially inner surface, the radially outer and inner surfaces defining an internal cavity therebetween. The nacelle further includes an aft nacelle segment translatable along a translation vector having an axial component, wherein the aft nacelle segment is configured to translate between a forward deployed position in which the nacelle defines a first primary fan nozzle exit area (A1) and a clean position in which the nacelle defines a second primary fan nozzle exit area (A2) less than the first primary fan nozzle exit area A1, wherein in the forward deployed position, the aft nacelle segment is at least partly located within the internal cavity.
    Type: Grant
    Filed: May 12, 2017
    Date of Patent: May 26, 2020
    Assignee: ROLLS -ROYCE PLC
    Inventor: John R Wells
  • Patent number: 10663036
    Abstract: The present disclosure is directed to a gas turbine engine, wherein the gas turbine engine defines a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline extended along the longitudinal direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes an annular stationary turbine frame centered around the axial centerline; an engine shaft extended generally along the longitudinal direction; an input shaft extended generally along the longitudinal direction; and a gear assembly including a first gear coupled to the input shaft, a second gear coupled to the turbine frame, and an inner spool coupling the first gear and the second gear, in which the inner spool defines a gear axis extended therethrough. The inner spool, the first gear, and the second gear are together rotatable about the gear axis. The gear axis is rotatable about the axial centerline of the engine.
    Type: Grant
    Filed: June 13, 2017
    Date of Patent: May 26, 2020
    Assignee: General Electric Company
    Inventors: Alan Roy Stuart, Darek Tomasz Zatorski
  • Patent number: 10655563
    Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.
    Type: Grant
    Filed: November 27, 2017
    Date of Patent: May 19, 2020
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Thierry Surply, Alain Porte, Patrick Oberle, Eric Haramburu, Thomas Sauvalle, Benoit Letay, Frédéric Piard, Vincent Billerot, Franck Oundjian
  • Patent number: 10648426
    Abstract: A thrust reverser system comprising a single row vane assembly is provided. The provided thrust reverser system is capable of meeting performance requirements for turbine engines with reduced weight and cost.
    Type: Grant
    Filed: January 14, 2016
    Date of Patent: May 12, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Danis Burton Smith, Mark Knowles, Shawn Alstad, Robert Romano, John Taylor Pearson, Morris Anderson, David Robinson
  • Patent number: 10648427
    Abstract: The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct by means of a camming surface, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: May 12, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nigel David Sawyers-Abbott, James Power
  • Patent number: 10641207
    Abstract: There is provided an air flow deflector apparatus for a thrust reverser system of an engine of an air vehicle. The air flow deflector apparatus is movable between a stowed non-reversing position and a deployed thrust reversing position, to deflect an air flow out of the engine, and to provide an effective reverse thrust for the thrust reverser system. There is further provided an air flow deflector assembly for a structure. The air flow deflector assembly has the air flow deflector apparatus, an extender member, and a recessed housing disposed in the structure. The air flow deflector assembly has an air flow deflector actuator that moves the air flow deflector apparatus between a stowed position and a deployed position adjacent to a reverse efflux air flow exit portion of the structure. The air flow deflector assembly deflects a reverse efflux air flow away from being re-ingested into the structure.
    Type: Grant
    Filed: July 21, 2017
    Date of Patent: May 5, 2020
    Assignee: The Boeing Company
    Inventors: Chen Chuck, Suk C. Kim