Axially Moved Discharge Portion Opens Side Outlet Patents (Class 239/265.31)
  • Patent number: 10914267
    Abstract: The present disclosure concerns a thrust reverser system for a turbojet engine and a method for unlocking a thrust reverser system. The thrust reverser system includes a movable cowl mounted on a nacelle of the turbojet engine that is displaceable between a closed position in which the thrust reverser system is inactivated and an open position in which the thrust reverser system is activated. The thrust reverser system includes a locking system having a first and second locking element mounted on the movable cowl and a fixed structure. The first and second locking elements lock and unlock relative to each other to lock the movable cowl on the fixed structure in the closed position. The locking system is shaped so that a controlled displacement of the movable cowl from its closed position to a reclosed position triggers unlocking of the first and second locking elements.
    Type: Grant
    Filed: April 16, 2018
    Date of Patent: February 9, 2021
    Assignee: Safran Aircraft Engines
    Inventor: Gabriel Allut
  • Patent number: 10844749
    Abstract: An aircraft propulsion assembly having a thrust reverser with moving guards, including an engine covered by a front cover and a rear cover that are both mobile; moving guards supported by the rear cover, the guards being covered by the front cover in normal operation, and extending into a space separating the front cover from the rear cover when the rear cover is moved to the rear; two arcuate frames, which are spaced apart and surround the engine in order to support actuators for moving the rear cover; the space located between the two arcuate frames being uncovered when the front and rear covers are moved to the front and rear; and wherein the two arcuate frames jointly support a series of elements forming steps which constitute a ladder for quick access to the top of the propulsion assembly.
    Type: Grant
    Filed: December 5, 2016
    Date of Patent: November 24, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Carmen Gina Ancuta, Bruna Manuela Ramos
  • Patent number: 10830089
    Abstract: A turbofan with a fan casing and a nacelle which comprises a fixed structure, a movable assembly with a movable cowl and a slide, which is translationally movable between an advanced position and a retreated position in which the movable cowl is moved away from the fan casing in order to define a window open between a duct and the outside of the nacelle, a plurality of blades, each being mounted rotatably on the slide, where each blade is movable between a retracted position in which the blade is outside of the duct and a deployed position in which the blade is across the duct, a set of actuators for moving the slide and an operating system configured to move each blade from the retracted position to the deployed position, and vice versa.
    Type: Grant
    Filed: February 21, 2019
    Date of Patent: November 10, 2020
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Pascal Gardes, Frédéric Ridray, Frédéric Piard
  • Patent number: 10753314
    Abstract: A nacelle includes a fixed structure supporting a fixed cowl and a movable cowl, the movable cowl being movable translationally between a closing position and an opening position. A blocker door is movably mounted rotationally on the nacelle between a closed position and an open position. The nacelle includes a drive mechanism of the blocker door and of the movable cowl between the closed/closing position and the open/opening position of the blocker door/movable cowl, respectively, and vice versa, the drive mechanism includes at least one actuator fixed, to the fixed structure of the nacelle and, to a fitting fixed to the movable cowl. The drive mechanism includes, for each actuator, a flexible member having a first end fixed to the fixed structure of the nacelle and a second end fixed to the fitting.
    Type: Grant
    Filed: February 6, 2018
    Date of Patent: August 25, 2020
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Eric Haramburu, Patrick Oberle, Eric Masson
  • Patent number: 10676204
    Abstract: A variable-orientation stator vane of a turbine engine, comprising a wall that extends between a leading edge and a trailing edge forming a chord line. The chord line increases from a root end towards a tip end of said vane. This vane is fitted pivotably in a turbine engine casing so as to divert a flow of cold air circulating in an annular duct thereof.
    Type: Grant
    Filed: November 15, 2016
    Date of Patent: June 9, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Kevin Morgane Lemarchand, Guillaume Olivier Vartan Martin
  • Patent number: 10669970
    Abstract: A thrust reverser system includes two thrust reversal cascades, of which the first cascade is entrained by an actuator, and which are configured to adopt a retracted position in which they are housed in a space located outside the duct. The action of the actuator brings about: rearward displacement of the first cascade in the direction of a nacelle opening; and during part of the rearward displacement of the second cascade, simultaneous pivoting of this second cascade under the action of a control lever, the interaction of which with a fixed guide rail forces the front end of the lever to move radially inwards while the lever is entrained rearwards by the second cascade.
    Type: Grant
    Filed: June 13, 2018
    Date of Patent: June 2, 2020
    Assignee: Airbus Operations S.A.S.
    Inventors: Olivier Pautis, Lionel Czapla
  • Patent number: 10619598
    Abstract: The present disclosure concerns a nacelle for an aircraft engine, which includes a thrust reverser cowling that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling opens a passage in the nacelle and uncovers a deflection device, and at least one actuator for moving the cowling. The nozzle section of the cowling delimits at least one opening that is combined with a leakage door, the leakage door being movably mounted on the cowling between a closed position in which the door engages with the associated opening to counteract the flow of air through said opening, and an open escape position in which the door is retracted to allow a portion of the air flow to flow through said opening.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: April 14, 2020
    Assignee: AIRCELLE
    Inventors: Peter Segat, Sarah Tissot, Xavier Bouteiller
  • Patent number: 10612490
    Abstract: A drag link assembly for use in a thrust reverser of a propulsion system is provided. The thrust reverser includes a fixed structure and a translating structure that at least partially define an annular airstream bypass duct there between. The translating structure is moveable relative to the fixed structure. The translating structure includes a blocker door disposed at least partially within the airstream bypass duct. The drag link assembly includes a drag link fitting and a drag link. The drag link fitting is fastened to the fixed structure of the thrust reverser. The drag link includes a first end portion and an opposing second end portion. The first end portion is pivotably connected to the blocker door. The second end portion is pivotably connected to the drag link fitting. The second end portion includes a curved section.
    Type: Grant
    Filed: April 25, 2014
    Date of Patent: April 7, 2020
    Assignee: Rohr, Inc.
    Inventor: Stuart J. Byrne
  • Patent number: 10605199
    Abstract: A lockable actuator includes: a body; a screw for pivoting relative to the body; a nut engaged on the screw so as to move along the screw between an over-retracted first position and a deployed second position on opposite sides of a retracted third position; a sleeve constrained to rotate with the screw and slidably mounted thereon in order to be moved by the nut; and an obstacle secured to the sleeve and a pawl capable of passing collectively between an active state and an inactive state, the pawl and the obstacle being arranged in such a manner that the pawl in its active state can co-operate with the obstacle only after the nut has been moved through a predetermined distance from its third position towards its second position.
    Type: Grant
    Filed: February 23, 2018
    Date of Patent: March 31, 2020
    Assignee: SAFRAN ELECTRONICS & DEFENSE
    Inventors: Mickael Werquin, Julien Hautecoeur, Christophe Bastide, Pascal Omnes
  • Patent number: 10563614
    Abstract: An improved translating cowl (transcowl) assembly for a thrust reverser system for a turbine engine is provided. The transcowl assembly comprises an outer skin comprised of a first composite material and an inner skin comprised of a second composite material. The inner skin is configured to couple circumferentially within the outer skin, and creates a flow path for engine exhaust flow. The inner skin comprises a contoured depression configured to provide clearance for movement of a blocker door. A metallic bracket is disposed between the inner skin and outer skin.
    Type: Grant
    Filed: August 17, 2016
    Date of Patent: February 18, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Danis Burton Smith, Patrick S. Mulloy, Shawn Alstad
  • Patent number: 10533521
    Abstract: There is provided an inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade assembly has inflatable cascade members for inflation with a pressurized fluid. The inflatable cascade members are movable between a stowed deflated state and a deployed inflated state. Each inflatable cascade member has a forward end, an aft end, and a body. The body has circumferential vanes each having a first non-inflatable rigid side attached adjacent to a second inflatable flexible side. The body further has inflatable support members that are spaced apart and longitudinally extending, and coupled in a perpendicular arrangement to the circumferential vanes. The body further has a plurality of flow openings defined between the circumferential vanes and the inflatable support members. Each inflatable cascade member further has first and second extendable side supports coupled to respective first and second side ends of the body.
    Type: Grant
    Filed: July 31, 2017
    Date of Patent: January 14, 2020
    Assignee: The Boeing Company
    Inventors: Naimishkumar B. Harpal, Chen Chuck, Zachariah B. Vandemark
  • Patent number: 10533519
    Abstract: Aspects are directed to a system associated with a thrust reverser of an aircraft, comprising: a blocker door and a fan case, where when the thrust reverser is stowed the blocker door is stowed at least in part radially outboard of the fan case. Aspects include a thrust reverser system comprising: a fixed structure, a translating sleeve configured to translate relative to the fixed structure, at least one blocker door pivotally mounted to the translating sleeve, and a rod coupled to the fixed structure and to the at least one blocker door, where during a first phase of thrust reverser deployment the blocker door translates with the translating sleeve when the translating sleeve is translating toward its deployed position and does not rotate, and during a second phase following the first phase, the blocker door pivots relative to the translating sleeve from a stowed position to a deployed position.
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: January 14, 2020
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 10519899
    Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: December 31, 2019
    Assignee: Airbus Operations (SAS)
    Inventors: Olivier Pautis, Jerome Colmagro
  • Patent number: 10502161
    Abstract: A thrust reverser system may comprise a cascade radially positioned about a centerline of an engine or a nacelle centerline. Various cascade features may be positioned at a constant radius from the centerline while other features vary according to station and/or circumferential position.
    Type: Grant
    Filed: November 30, 2015
    Date of Patent: December 10, 2019
    Assignee: ROHR, INC.
    Inventor: Sara C. Crawford
  • Patent number: 10473057
    Abstract: A thrust reverser system is provided with an axial centerline. This thrust reverser system includes a first translating element, a second translating element and an actuator mechanism. The actuator mechanism is attached to the first translating element and the second translating element. The actuator mechanism is configured to translate the first translating element along the axial centerline at a first rate. The actuator mechanism is configured to translate the second translating element along the axial centerline at a second rate, which may be different than the first rate.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: November 12, 2019
    Assignee: Rohr, Inc.
    Inventor: Michael Aten
  • Patent number: 10451004
    Abstract: A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: October 22, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Patent number: 10451002
    Abstract: A thrust reverser system for a turbine engine includes a support structure, a transcowl, a door, and an anti-rotation structure. The transcowl is mounted on the support structure and has an inner surface. The transcowl is axially translatable, relative to the support structure, between first and second positions. The door is pivotally coupled to the turbine engine, and has a forward edge and an aft edge. The door is rotatable between stowed and deployed positions when the transcowl translates between the first and second positions, respectively. The anti-rotation structure extends from the transcowl and is disposed adjacent to the aft edge of the door when the transcowl is in the first position and the door is in the stowed position. The anti-rotation structure is configured such that door rotation out of the stowed position only occurs subsequent to or concurrently with translation of the transcowl out of the first position.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: October 22, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Danis Burton Smith, Mark Knowles, Robert Romano, Shawn Alstad, David Robinson
  • Patent number: 10309343
    Abstract: A system for a thrust reverser of an aircraft includes a primary sleeve and a secondary sleeve having cascades. The secondary sleeve is coupled to a set of blocker doors. The sliding motions of the primary sleeve and the secondary sleeve are not directly coupled when each moves between its stowed and deployed positions. The sliding motion of the primary sleeve may begin at a different time and continue at a different rate from the sliding motion of the secondary sleeve.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: June 4, 2019
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 10208708
    Abstract: Aspects of the disclosure are directed to a thrust reverser system of an aircraft comprising: a translating cascade sleeve, a blocker door, and a kinematic mechanism configured to actuate the blocker door, the kinematic mechanism comprising: a first link coupled to the translating cascade sleeve, a second link coupled to the first link and a fixed structure, and a third link coupled to the first link and the blocker door.
    Type: Grant
    Filed: January 29, 2015
    Date of Patent: February 19, 2019
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 10202940
    Abstract: An engine cowling of an aircraft gas turbine with a front area and a rear area that is displaceable in the axial direction, characterized in that the rear area is mounted and supported by means of multiple length-adjustable thrust reversal actuators that are arranged at an angle to one another.
    Type: Grant
    Filed: April 7, 2016
    Date of Patent: February 12, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Predrag Todorovic
  • Patent number: 10184358
    Abstract: A retractable exhaust liner segment according to an example of the present disclosure includes, among other things, at least one liner segment extending between a forward end and an aft end. The forward end of the at least one liner segment is configured to overlap an aft end of an engine structure and the aft end of the at least one liner segment is configured to overlap a forward end of an exhaust liner when in an assembled position. The at least one liner is configured such that a gap exists between the at least one liner segment and one of the engine structure and the exhaust liner when the at least one liner segment is moved along an axis in a first direction to a disassembled position. The gap closes as the at least one liner segment is moved along the axis in a second, different direction to the assembled position.
    Type: Grant
    Filed: July 24, 2015
    Date of Patent: January 22, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Dale William Petty
  • Patent number: 10167816
    Abstract: An engine cowling of an aircraft gas turbine with a front area and a rear area that is displaceable in the axial direction, characterized in that the rear area is mounted and supported by means of multiple length-adjustable thrust reversal actuators that are arranged at an angle to one another.
    Type: Grant
    Filed: April 7, 2016
    Date of Patent: January 1, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Predrag Todorovic
  • Patent number: 10161356
    Abstract: A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie.
    Type: Grant
    Filed: June 2, 2014
    Date of Patent: December 25, 2018
    Assignee: GE Aviation Systems LLC
    Inventors: John S. Mears, George Stephen Billisits, Chad Russell Wentling
  • Patent number: 10066582
    Abstract: An engine cowling of an aircraft gas turbine having a front cowling and a single rear cowling movable in the axial direction. By a drive device, the rear cowling is movable into different positions including a closed cruise position, a partially opened maximum thrust position and a completely opened thrust-reversing position. The drive device includes at least two actuators arranged in series relative to one another and actuated independently of one another, the actuators having power supply systems separated from one another and separately operating, where one of the actuators is designed for the maximum thrust position and the other actuator for the thrust-reversing position. The rear cowling can be locked in the maximum thrust position or the thrust-reversing position by two independent locking devices.
    Type: Grant
    Filed: November 11, 2015
    Date of Patent: September 4, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag Todorovic
  • Patent number: 10006405
    Abstract: A thrust reverser system and operation suitable for turbofan engines. Blocker doors of the thrust reverser system have stowed positions in which each door is disposed between a fixed structure and a translating cowl of the engine. The translating cowl is translated in an aft direction of the engine to define at least one opening with the fixed structure, after which the translating cowl is further translated aft to deploy linkage mechanisms that are received in slots recessed into the blocker doors and pivotably connect the doors to the fixed structure. Deployment of the linkage mechanisms from the slots causes the blocker doors to rotate to a deployed position in which each door extends across a bypass duct of the engine and diverts bypass air within the duct through the opening.
    Type: Grant
    Filed: November 30, 2012
    Date of Patent: June 26, 2018
    Assignee: General Electric Company
    Inventors: Alan Roy Stuart, James Michael Cosgrove
  • Patent number: 9944401
    Abstract: An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser includes an upper blocker door movable about a first pivot axis to a deployed position and a lower blocker door movable about a second pivot axis not parallel to the first pivot axis.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: April 17, 2018
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Chandler, Gabriel L. Suciu
  • Patent number: 9915226
    Abstract: A thrust reverser of an aircraft comprises a blocker door and a variable area fan nozzle (VAFN) panel configured to conceal the blocker door from a duct associated with a bypass fan flow when the VAFN panel is in a closed position.
    Type: Grant
    Filed: June 18, 2015
    Date of Patent: March 13, 2018
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 9835038
    Abstract: In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration.
    Type: Grant
    Filed: August 7, 2013
    Date of Patent: December 5, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Vincent Paradis, John Walter Pietrobon, Richard L. Bouchard
  • Patent number: 9822733
    Abstract: A thrust reverser of a propulsion system nacelle is provided. The thrust reverser includes a fixed structure, a translating structure, and an aerodynamic feature. The fixed structure includes an annular wall that partially defines an annular bypass airstream duct. The fixed structure is bifurcated into left and right side sections. The annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section. The translating structure is moveable relative to the fixed structure, between a stowed position and a deployed position. The aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls. The flange aids in preventing aerodynamic drag.
    Type: Grant
    Filed: April 25, 2014
    Date of Patent: November 21, 2017
    Assignee: Rohr, Inc.
    Inventor: Stuart J. Byrne
  • Patent number: 9803586
    Abstract: A control system for a variable area fan nozzle (VAFN) is disclosed. The VAFN may have a plurality of petals and may be for use with a gas turbine engine. The control system may include a primary system configured to acquire primary data indicative of an operating condition of the VAFN, a secondary system configured to acquire secondary data indicative of a current operating condition of the gas turbine engine, and a control module in operative communication with the primary system and the secondary system. The control module may be configured to: determine a nozzle area of the VAFN based at least in part on the primary data, adjust the determined nozzle area based on the secondary data, and position the plurality of petals according to the adjusted nozzle area.
    Type: Grant
    Filed: May 31, 2016
    Date of Patent: October 31, 2017
    Assignee: The Boeing Company
    Inventors: Jason J. Jackowski, Kent E. Karnofski, David W. Foutch
  • Patent number: 9803587
    Abstract: A method of fabricating a bonded cascade assembly of a thrust reverser for an aircraft nacelle. The method may include inserting individual turning vanes between spaced apart elongated stiffeners at an aft end thereof and sliding the turning vanes toward a front frame piece attached to or integrally formed with forward ends of the elongated stiffeners. The elongated stiffeners may have inner and outer flanges for trapping and limiting radial movement of the turning vanes. The method may further include bonding the turning vanes to the structural frame with a structural adhesive and attaching a closeout cap to the aft ends of each of the elongated stiffeners.
    Type: Grant
    Filed: November 2, 2016
    Date of Patent: October 31, 2017
    Assignee: Spirit AeroSystems, Inc.
    Inventors: Henry A. Schaefer, Mark A. Wadsworth
  • Patent number: 9777670
    Abstract: The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream.
    Type: Grant
    Filed: January 28, 2014
    Date of Patent: October 3, 2017
    Assignee: AIRCELLE
    Inventor: Pierre Caruel
  • Patent number: 9777671
    Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.
    Type: Grant
    Filed: February 18, 2013
    Date of Patent: October 3, 2017
    Assignee: ROHR, INC.
    Inventors: Jihad I. Ramlaoui, Geoffrey Pinto, Daniel Shetzer, Daniel M. Amkraut, Andrew Robert Hawksworth, John Harvey, Alan K. Evans, Vikram Chandarana, Roger Moorhouse
  • Patent number: 9777598
    Abstract: A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: October 3, 2017
    Assignee: AIRCELLE
    Inventors: Jean-Philippe Joret, Xavier Bouteiller, Xavier Cazuc, Pierre Caruel
  • Patent number: 9759158
    Abstract: A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The bypass flow defines a bypass ratio greater than about six (6). The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow.
    Type: Grant
    Filed: December 21, 2011
    Date of Patent: September 12, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATIO
    Inventor: Richard M. Marshall
  • Patent number: 9701415
    Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle axially movable relative the fan nacelle to define an auxiliary port to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
    Type: Grant
    Filed: December 8, 2011
    Date of Patent: July 11, 2017
    Assignee: United Technologies Corporation
    Inventors: Gregory A. Kohlenberg, Sean P. Zamora
  • Patent number: 9593643
    Abstract: The invention relates to a device (3) for driving actuators (7-10) for a thrust reverser, comprising a motorized drive unit (15), a brake (16) and a manual drive unit (17) for rotatably driving a drive shaft, and a control part (44) which can be actuated by an operator, the control part (44) being mobile between a motorized drive position and a manual drive position, the movement of the control part (44) from the motorized drive position into the manual drive position causing the movement of a clutch part (40) into an engaged position in order to connect the manual drive unit (17) to the drive shaft (14), and the movement of the brake (16) into the loosened configuration in order to authorize the driving of the drive shaft (14) in rotation by the manual drive unit (17).
    Type: Grant
    Filed: September 9, 2014
    Date of Patent: March 14, 2017
    Assignee: SAGEM DEFENSE SECURITE
    Inventor: Julien Tisseau
  • Patent number: 9551298
    Abstract: A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil.
    Type: Grant
    Filed: July 24, 2013
    Date of Patent: January 24, 2017
    Assignee: Rohr, Inc.
    Inventors: Alan Binks, Michael J. Layland, Norman J. James
  • Patent number: 9212624
    Abstract: A cascade assembly is provided for installation in an aircraft nacelle. The cascade assembly comprises a first cascade portion fixed to a non-movable portion of the nacelle. The first cascade portion comprises a bracket. A second cascade portion is fixed to a translating sleeve portion of the nacelle. The second cascade portion comprises a catch. The bracket is configured to receive the catch in response to the translating sleeve portion being in a deployed position.
    Type: Grant
    Filed: May 6, 2013
    Date of Patent: December 15, 2015
    Assignee: ROHR, INC.
    Inventor: Michael Aten
  • Patent number: 9188025
    Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a mounting assembly including at least one power drive system. The fan cowl is movable with respect to the engine along the axis toward at least one of the inlet end and the exhaust end.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: November 17, 2015
    Assignee: MRA Systems, Inc.
    Inventors: David P. Calder, Graham F. Howarth
  • Patent number: 9016042
    Abstract: An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.
    Type: Grant
    Filed: May 11, 2012
    Date of Patent: April 28, 2015
    Assignee: Rohr, Inc.
    Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland
  • Patent number: 8973364
    Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
    Type: Grant
    Filed: June 26, 2008
    Date of Patent: March 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Jonathan Gilson, Dennis Cicon, Oliver V. Atassi
  • Patent number: 8943794
    Abstract: The invention relates to a linear telescopic actuator for moving a first (10b) and a second (10a) element relative to a stationary element (102). Said actuator comprises a base (101) that is to be connected to the stationary element (102) and is used as a cavity for a first rotationally locked rod (106) which can be translated by a drive shaft (104) that is to be connected to rotational driving means (107). One end (108) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod (106) supports a second rod (117) which is aligned therewith and one end (118) of which is to be connected to the second element that is to be moved. Said second rod (117) can be rotationally locked and can be translated by a second drive shaft (112, 115) which extends through the base and is connected to rotational driving means (113, 111).
    Type: Grant
    Filed: July 4, 2008
    Date of Patent: February 3, 2015
    Assignee: Aircelle
    Inventors: Pierre Moradell-Casellas, Pierre Andre Marcel Baudu, Guy Bernard Vauchel
  • Publication number: 20140366554
    Abstract: A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section.
    Type: Application
    Filed: August 29, 2014
    Publication date: December 18, 2014
    Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
  • Patent number: 8904751
    Abstract: A thrust reverser assembly and operation suitable for high-bypass turbofan engines. The thrust reverser assembly includes a translating cowl mounted to a nacelle of an engine and adapted to translate in an aft direction of the engine. The translating cowl has a radially inner wall that defines a radially outer flow surface of a bypass duct of the engine. The thrust reverser assembly includes blocker doors axially guided adjacent first ends thereof by a fixed structure and pivotally and slidably connected along lengths thereof to the inner wall of the translating cowl so that translation of the translating cowl in the aft direction causes each blocker door to move from a stowed position to a deployed position as a result of the blocker door sliding at its first end relative to the fixed structure and sliding along its length relative to the inner wall of the translating cowl.
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: December 9, 2014
    Assignee: Middle River Aircraft Systems
    Inventors: Graham Frank Howarth, Bryan Wayne Hughes
  • Patent number: 8800262
    Abstract: The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion (15) downstream from which is mounted at least one cowl (9) movable between a direct-jet position, in which the cowl (9) is aligned with the stationary portion (15), and a thrust-reversal position, in which the mobile cowl (9) is spaced apart from the stationary portion (15) so as to define an opening for the passage of a secondary flow (F), a means for deflecting (16) the secondary flow (F) through the passage opening, an actuator means (45) and a means (24) for guiding the mobile cowl (9) relative to the stationary portion (15), at least a first and a second adjacent cascade vane (13), positioned at an angle (B) relative to the movement axis (A) of the mobile cowl (9), arranged opposite the passage opening such that the deflected secondary flow (F) at least partially passes through the first and second vanes (13) in order to increase the deflection of said secondary flow (F) in the upstream direction, sai
    Type: Grant
    Filed: November 23, 2009
    Date of Patent: August 12, 2014
    Assignee: Aircelle
    Inventors: Guy Bernard Vauchel, Pierre Caruel
  • Patent number: 8783614
    Abstract: The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second hath-shells rotatably mounted about an axis such that they can each be deployed between a working position in which the half-shells are drawn towards one another and a maintenance position in which the half-shells are spaced apart, at least the first half-shell (11) being equipped with a first follower element (19) in a region situated at a distance from the axis of rotation, the nacelle being equipped with a first fixed guide element (28), the first follower element (19) being designed to bear against a first guide element (28) which is fixed with respect to the jet engine during the rotation of the first half-shell (11).
    Type: Grant
    Filed: June 12, 2008
    Date of Patent: July 22, 2014
    Assignee: Aircelle
    Inventor: Gilles Bourdon
  • Patent number: 8739515
    Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners therebetween to increase a flutter margin.
    Type: Grant
    Filed: November 24, 2009
    Date of Patent: June 3, 2014
    Assignee: United Technologies Corporation
    Inventors: Fred W. Schwark, Jr., Oliver V. Atassi, William D. Owen
  • Patent number: 8733080
    Abstract: An actuator arrangement comprises an actuator having a rotatable drive input, a motor, and a drive transmission arrangement for transmitting rotary drive from the motor to the rotatable drive input of the actuator, wherein the transmission arrangement includes a telescopic drive coupling.
    Type: Grant
    Filed: March 28, 2008
    Date of Patent: May 27, 2014
    Assignee: Goodrich Actuation Systems Limited
    Inventors: Tony Jones, John Herbert Harvey, Peter William Bacon, Mark Hubberstey, Brett John Wharton, Neil Charles Davies, Stephen Michael Roberts, Steven Andrew Wylie
  • Patent number: 8511062
    Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.
    Type: Grant
    Filed: June 16, 2009
    Date of Patent: August 20, 2013
    Assignees: Rohr, Inc., Goodrich Actuation Systems Limited
    Inventors: Jihad I. Ramlaoui, Geoffrey Pinto, Daniel Shetzer, Daniel M. Amkraut, Andrew Robert Hawksworth, John Harvey, Alan K. Evans, Vikram Chandarana, Roger Moorhouse