Controller Moves Into Fluid Path From Position Closing One Outlet Patents (Class 239/265.29)
  • Patent number: 11028801
    Abstract: A grating for the formation of a reverse flow of a turbofan engine and comprising fins of a first type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the first type, fins of a second type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the second type. In this grating, each fin of one of the two types is inserted between two fins of the other type moving from forward to aft and the cord of the fins of the second type is smaller than the cord of the fins of the first type.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: June 8, 2021
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Christophe Bourdeau, Quentin Vaucouloux, Romain Cusset
  • Patent number: 10954889
    Abstract: A thrust reverser actuation system for a jet propulsion engine for a vehicle, the thrust reverser actuation system comprising: a plurality of hydraulically-driven thrust reverser actuators for actuating one or more thrust reverser components of the jet propulsion engine, each actuator comprising: a hydraulic circuit; and a bi-directional electrically-driven pump configured to pump hydraulic fluid through the hydraulic circuit, wherein the hydraulic circuit and the pump are configured such that the direction of the pump dictates the direction of the actuation of the actuator.
    Type: Grant
    Filed: December 11, 2017
    Date of Patent: March 23, 2021
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventors: Tim Hudson, Nicholas Sloane
  • Patent number: 10907576
    Abstract: A nacelle for a gas turbine engine, comprising a thrust reverser movable between a stowed position and a deployed position, and a locking system configured to selectively prevent movement of the thrust reverser from the stowed position, the locking system comprising a locking mechanism and an actuator configured to actuate the locking mechanism, wherein the locking mechanism is positioned aft of a blade-off zone defined across the nacelle and the actuator is positioned fore of, or at least partially within, the blade-off zone.
    Type: Grant
    Filed: April 27, 2018
    Date of Patent: February 2, 2021
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventors: Antony Morgan, Michael Paul Somerfield
  • Patent number: 10814997
    Abstract: This disclosure relates to a support device for an actuator. The support device includes a support unit adapted to be mounted to a stationary structure, an attachment unit adapted to be attached to an actuator casing and a single pivot shaft, and the attachment unit is pivotably connected to the support unit via the single pivot shaft. The support device according to the present disclosure has a simple structure and is stable in operation. The present disclosure further relates to an air intake system for an auxiliary power unit, which includes the above support device for the actuator. In addition, the present disclosure further relates to an aircraft including the air intake system for the auxiliary power unit.
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: October 27, 2020
    Assignee: AIRBUS (S.A.S.)
    Inventors: Feng Zhang, Na Shi, Ying An
  • Patent number: 10724473
    Abstract: A system for actuating a blocker door of a thrust reverser, in which a drag link assembly is removed from the airflow through the engine during flight. The assembly couples the door to a sleeve so that translation of the sleeve between deployed and stowed positions moves the door to open and closed positions, respectively. The assembly includes a telescoping drag link having one end rotatably coupled with a drag link anchor and another end coupled with the door. During deployment and stowage, translation of the sleeve causes the door to move and the link to extend or collapse and rotate until it contacts a stop element of the anchor, and then rotate in the opposite direction as the door opens or closes, respectively. A channel may be provided in the door to accommodate the link. The anchor may include a spring which exerts a rotational force on the link.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: July 28, 2020
    Assignee: Spirit AeroSystems, Inc.
    Inventor: Alexander Jon Carr
  • 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: 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: 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: 10677192
    Abstract: A gas turbine engine system according to an exemplary aspect of the present disclosure may include a fan nacelle that extends circumferentially about a fan, and at least one integrated mechanism coupled to the fan nacelle. The at least one integrated mechanism includes a variable fan nozzle and a thrust reverser, with the thrust reverser and the variable fan nozzle having a common part.
    Type: Grant
    Filed: August 11, 2017
    Date of Patent: June 9, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Richard M. Marshall
  • Patent number: 10669971
    Abstract: A thrust reverser for a turbojet engine nacelle includes movable cowls which move backward relative to a front frame under the action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close the annular cold air flow path, and by opening cascades disposed around this flow path and which receive the cold air flow and return it forward. When the thrust reverser is closed, the cascades are partially integrated in the cowls, and the thrust reverser includes an actuation system which makes the cascades move backward along a stroke which is shorter than the stroke of the cowl.
    Type: Grant
    Filed: December 22, 2015
    Date of Patent: June 2, 2020
    Assignee: AIRCELLE
    Inventor: Pierre Caruel
  • Patent number: 10641208
    Abstract: A thrust reverser for a gas turbine engine includes a reverser door pivotally mounted to a frame, an exhaust duct translationally mounted to the frame and an actuator having an actuator rod connected to the reverser door and to the exhaust duct.
    Type: Grant
    Filed: November 27, 2017
    Date of Patent: May 5, 2020
    Assignee: ROHR, INC.
    Inventor: Anthony Lacko
  • Patent number: 10605197
    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, 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 1, 2015
    Date of Patent: March 31, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nigel David Sawyers-Abbott, James Power
  • Patent number: 10598127
    Abstract: A method of fabricating a thrust reverser cascade assembly including positioning a first frame section on an assembly fixture, positioning a first set of turning vanes on a first elongated stiffener of the first frame section, securing the first set of turning vanes to the elongated stiffener, positioning a second frame section on the assembly fixture adjacent to the first frame section such that the first set of turning vanes are between the elongated stiffeners of the first and second frame section, adding additional sets of turning vanes and frame sections, and fastening the frame sections together.
    Type: Grant
    Filed: August 15, 2017
    Date of Patent: March 24, 2020
    Assignee: Spirit AeroSystems, Inc.
    Inventors: Mark Anthony Wadsworth, Henry Arnold Schaefer
  • Patent number: 10590885
    Abstract: Thrust reversers and methods to provide reverse thrust are disclosed. An example thrust reverser includes a cascade to direct air from an interior volume of an engine nacelle to generate reverse thrust with respect to a direction of travel, and an air extractor to extract a portion of air approaching the cascade from within the interior volume.
    Type: Grant
    Filed: November 14, 2016
    Date of Patent: March 17, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Kurt Erik Acheson, Chen Chuck
  • Patent number: 10563615
    Abstract: A gas turbine engine and thrust reverser assembly having a set of outer doors movable between a stowed position and a deployed position, where the set of outer doors extends outwards from the nacelle and a set of blocker doors movable between a stowed position and an deployed position, where the set of blocker door extends into an air flow conduit defined by the bypass duct to deflect air outwards.
    Type: Grant
    Filed: May 9, 2016
    Date of Patent: February 18, 2020
    Assignee: MRA SYSTEMS, LLC
    Inventors: Graham Frank Howarth, Andrew Michael Roach, Timothy Robert Beasman
  • Patent number: 10486820
    Abstract: Systems for thrust reverser link arm connections are described herein. A linkage system for a nacelle may comprise a thrust reverser link arm and a fitting. The fitting may comprise a base plate configured to be fastened to a proximal surface of an inner fixed structure (IFS), a first wall extending orthogonally from the base plate, a second wall extending orthogonally from the base plate, and a pin extending orthogonally from the first wall and extending orthogonally from the second wall. A first end of the thrust reverser link arm may comprise a removable member, the removable member having an inner surface comprising a semi-circle, the inner surface configured to seat against the pin. The removable member may be removed from the linkage system from a radially outward side of the IFS.
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventor: Nigel David Sawyers-Abbott
  • Patent number: 10480453
    Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a retaining member having a first end and a second end and defining a first aperture and a cavity, wherein the pivot is configured to extend at least partially into the first aperture and the cavity is configured to accommodate a portion of the link arm, and wherein the retaining member comprises an attachment aperture located at the first end and a lip extending from the retaining member at the second end, the attachment aperture configured to receive a fastener and the lip configured to be placed under a distal layer of an inner fixed structure (IFS).
    Type: Grant
    Filed: September 7, 2016
    Date of Patent: November 19, 2019
    Assignee: United Technologies Corporation
    Inventors: Nigel David Sawyers-Abbott, Matthew Exner
  • Patent number: 10465538
    Abstract: A gas turbine engine having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct for airflow generated by the fan. The fan cowl includes an aft edge that defines a physical flow area of the bypass duct, and a deflection device configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine.
    Type: Grant
    Filed: October 2, 2015
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Darek Tomasz Zatorski, Patrick John Lonneman, Alan Roy Stuart
  • Patent number: 10442543
    Abstract: The invention relates to an engine cowling of an aircraft gas turbine which has a rear area that comprises at least two doors that are arranged at the bottom area of the rear area of the engine cowling and are to be opened by means of overhead hinges, wherein the hinges are arranged so as to be tilted with respect to the engine axis.
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: October 15, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag Todorovic
  • Patent number: 10443541
    Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, and an actuator. The transcowl is mounted on the support structure and is axially translatable between a stowed position and a deployed position. The actuator is coupled to the transcowl and the support structure, and is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The actuator includes an actuator housing, a screw, a nut, a rod end, and a tension rod. The tension rod is engaged by the nut when the transcowl is in the deployed position and is engaged by the rod end when the transcowl is in the stowed position, whereby actuator loads, in both the deployed and stowed positions, are transmitted through the tension rod to the support structure.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: October 15, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Kevin K Chakkera, Daniel C Birchak, Donald Jeffrey Christensen, James Wawrzynek
  • Patent number: 10400621
    Abstract: A gas turbine engine includes a nacelle assembly having a core nacelle defined about an engine axis and a fan nacelle assembly mounted at least partially around the core nacelle to define a fan bypass flow path. The fan nacelle assembly includes a fan duct nacelle section and a fan nozzle nacelle section moveable relative to the fan duct nacelle section. A thrust reverser system includes a plurality of pivot doors movable relative to the fan nacelle assembly between stowed and deployed positions. A variable area fan nozzle is in communication with the fan bypass flow path. A first actuator is mounted to the fan duct nacelle section to actuate the pivot door thrust reverser system, and a second actuator is mounted to the fan duct nacelle section to move the fan nozzle nacelle section relative to the fan duct nacelle section to vary a fan nozzle exit area.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: September 3, 2019
    Assignee: United Technologies Corporation
    Inventors: Nigel David Sawyers-Abbott, Constantino V. Loffredo
  • Patent number: 10378479
    Abstract: A turbofan engine is provided having a fan and a core in flow communication with the fan. The turbofan engine also includes a nacelle assembly enclosing the fan and at least a portion of the core to define a bypass passage with the core. The nacelle assembly includes a fan cowl extending around the fan and a thrust reverser system. The thrust reverser system is movable between a fully stowed position, a partially deployed position, and a fully deployed position. The thrust reverser system is configured to be held in the partially deployed position to allow an additional amount of airflow to exit from the bypass passage.
    Type: Grant
    Filed: October 19, 2015
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Matthew Timothy Franer, Brandon Wayne Miller
  • Patent number: 10344709
    Abstract: A system and method for reducing idle thrust in a translating cowl reverser system is provided. The provided system and method provide a partial deployment, or thrust reverser system intermediate position for a translating cowl thrust reverser system.
    Type: Grant
    Filed: September 10, 2015
    Date of Patent: July 9, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Danis Burton Smith, Shawn Alstad, Robert Romano, Mark Knowles, David Robinson
  • Patent number: 10316793
    Abstract: A thrust reverser actuator system fitting and a v-blade may be coupled to a track beam. A portion of the load between a translating sleeve and a fan case may be transmitted through the track beam. The thrust reverser actuator system fitting may comprise an integral v-blade.
    Type: Grant
    Filed: March 11, 2016
    Date of Patent: June 11, 2019
    Assignee: Rohr, Inc.
    Inventor: Sara C. Crawford
  • Patent number: 10309341
    Abstract: Systems and methods are provided for a formed thrust reverser cascade. The formed thrust reverser cascade may be coupled to an aircraft propulsor and may include a first portion disposed at a first angle to a portion of the aircraft propulsor and a second portion disposed at a second angle to the first portion. The formed thrust reverser cascade may be circumferentially disposed around a core engine of the aircraft propulsor. The formed thrust reverser cascades may be retrofitted to aircraft propulsors using linear thrust reverser cascade and may increase airflow through the formed thrust reverser cascade due to a greater throat area as compared to the linear thrust reverser cascade. Alternatively, the formed thrust reverser cascades may allow for shorter cascades while retaining the same performance, thus resulting in shorter nacelles.
    Type: Grant
    Filed: January 15, 2016
    Date of Patent: June 4, 2019
    Assignee: The Boeing Company
    Inventors: Naimishkumar B. Harpal, Chen Chuck
  • Patent number: 10302044
    Abstract: Aspects of the disclosure are directed to a system associated with a thrust reverser of an aircraft, comprising: a set of cascades incorporating a track, the track including a first track end and a second track end, a blocker door, and a link including a first link end coupled to the track and a second link end coupled to the blocker door, where the cascades are configured to translate between a stowed position and a deployed position to cause the first link end to traverse the track.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: May 28, 2019
    Assignee: Rohr, Inc.
    Inventor: Johann S. Schrell
  • Patent number: 10294893
    Abstract: A system and method for monitoring a thrust reverser system are provided. The embodiments described herein utilize sensors located proximate locks comprising a thrust reverser locking system. The provided system and method detect deflection and displacement proximate the locks to determine when individual locks have failed.
    Type: Grant
    Filed: May 25, 2016
    Date of Patent: May 21, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Danis Burton Smith, Robert Romano, Kevin K. Chakkera
  • Patent number: 10227951
    Abstract: An engine assembly includes a nacelle configured to at least partially surround an engine and a thrust reverser coupled to the nacelle. The thrust reverser includes: a thrust-reversing element movable relative to the nacelle between a stowed position and a deployed position; a hydraulic actuator operably coupled to move the thrust-reversing element; and a fluid control system configured to operate the hydraulic actuator. The fluid control system includes: a directional control unit including a directional control valve operable to selectively route fluid between a pressurized fluid source, the actuator, and a fluid return reservoir; one or more bypass fluid lines providing fluid communication between the actuator and the fluid return reservoir independent of the directional control valve; and a flow limiter residing between the pressurized fluid source and the directional control valve, the flow limiter configured to inhibit a pressure draw by the actuator from surpassing a predetermined threshold.
    Type: Grant
    Filed: February 2, 2017
    Date of Patent: March 12, 2019
    Assignee: Woodward, Inc.
    Inventor: Joseph Thomas Kopecek
  • Patent number: 10226651
    Abstract: A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.
    Type: Grant
    Filed: January 26, 2017
    Date of Patent: March 12, 2019
    Assignee: Safran Aero Boosters SA
    Inventors: Nicolas Raimarckers, Gaetano Taccogna
  • Patent number: 10184426
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a thrust reverser cascade, a fan ramp fairing and a blocker door. The thrust reverser cascade extends along an axial centerline from a forward cascade end to an aft cascade end. The fan ramp fairing is disposed at the forward cascade end. The fan ramp fairing is configured with a fairing surface that provides a forward boundary for bypass air flowing into the thrust reverser cascade during a first mode of operation. The blocker door is configured to completely axially overlap the fairing surface during a second mode of operation.
    Type: Grant
    Filed: June 22, 2015
    Date of Patent: January 22, 2019
    Assignee: Rohr, Inc.
    Inventor: Johann S. Schrell
  • Patent number: 10138843
    Abstract: A thrust reverser operable within a flowpath defined in-part by a surface carried by a fixed structure includes a translating sleeve constructed and arranged to move between first and second positions and a blocker door pivotally engaged to the translating sleeve for pivotal movement between a first state and a second state. A drag link assembly of the thrust reverser includes a base joint, a mid joint, and a distal joint. A base link extends between the base and mid joints, and a drag link extends between the mid and distal joints. The base joint operably connects the base link to the fixed structure, the mid joint operably connects the base link to the drag link, and the distal joint operably connects the drag link to the blocker door. The base joint and the mid joint are disposed beneath the surface when the blocker door is in the first state.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: November 27, 2018
    Assignee: ROHR, INC.
    Inventor: Timothy Gormley
  • Patent number: 10094286
    Abstract: A gas turbine engine includes a nacelle, a lower bifurcation structure, and a heat exchanger. The nacelle extends circumferentially around an engine core and defines a fan bypass duct that is substantially annular between an inner wall and an outer wall. The lower bifurcation structure extends between the inner wall and the outer wall, bifurcating the fan bypass duct. The lower bifurcation structure defines a bifurcation duct extending along a central axis of the lower bifurcation structure. A heat exchanger is positioned in the bifurcation duct.
    Type: Grant
    Filed: January 29, 2013
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventor: Matthew J. Forcier
  • Patent number: 10087842
    Abstract: A turbojet engine nacelle includes a fixed structure, which has a fan casing of the turbojet engine and a front frame mounted downstream of the fan casing and directly or indirectly supporting cascade vanes. The front frame is able to collaborate with a thrust reverser cowling sliding between a closed position covering the flow-diverting means and an open position exposing this flow-diverting means. At least one reinforcing structure of the engine nacelle transmits load between the fan casing and the front frame. The reinforcing structure extends along the longitudinal axis of the nacelle and supports a third line of defense and/or an inhibiting device between the front frame and the thrust reverser cowling.
    Type: Grant
    Filed: May 15, 2013
    Date of Patent: October 2, 2018
    Assignee: AIRCELLE
    Inventor: Pierre Caruel
  • Patent number: 10072609
    Abstract: In various embodiments, the thrust vectoring systems described herein create variable reverse thrust during a landing event. The reverse thrust may be varied based on manual inputs, dynamically changing operating events, or a landing duty cycle. In various embodiments, the thrust vectoring systems comprise a movable shelf that is capable of adjusting a directing a fluid flow to create a variable reverse thrust which may reduce the risk of foreign object ingestion in the engine at lower ground speeds.
    Type: Grant
    Filed: September 15, 2015
    Date of Patent: September 11, 2018
    Assignee: ROHR, INC.
    Inventor: Norman J. James
  • Patent number: 9970388
    Abstract: A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.
    Type: Grant
    Filed: May 4, 2017
    Date of Patent: May 15, 2018
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Chandler, Gabriel L. Suciu
  • Patent number: 9926884
    Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: March 27, 2018
    Assignee: Rohr, Inc.
    Inventors: Sara Christine Crawford, Michael Aten, Anthony Lacko
  • Patent number: 9920709
    Abstract: Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: March 20, 2018
    Assignee: Rohr, Inc.
    Inventors: Joel H. Frank, Lubomir A. Ribarov
  • Patent number: 9856825
    Abstract: A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes.
    Type: Grant
    Filed: August 8, 2012
    Date of Patent: January 2, 2018
    Assignee: SNECMA
    Inventor: Francois Gallet
  • Patent number: 9834313
    Abstract: The present disclosure relates to a front frame for an aircraft nacelle comprising a turbojet mounted on a suspension strut, said nacelle comprising a thrust reverser including an actuator designed to open a thrust reversal cowling. The front frame comprises a tubular torsion box, a first straight attachment edge intended to attach the box to a turbojet casing and a second straight attachment edge intended to attach the box to air flow diversion means. The front frame is arranged to transmit tensile and compressive loads between the turbojet casing and the air flow diversion means and torsion loads absorbed by the suspension strut. The front frame is characterized in that the tubular torsion box has a semi-elliptical or elliptical cross-section.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: December 5, 2017
    Assignee: AIRCELLE
    Inventors: Xavier Cazuc, Jean-Philippe Joret
  • Patent number: 9783315
    Abstract: A nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The nacelle also includes a second cowling that at least partially defines the inlet and which translates relative to the first cowling. The nacelle can include a third cowling that at least partially defines the outlet and translates relative to the first cowling.
    Type: Grant
    Filed: February 24, 2012
    Date of Patent: October 10, 2017
    Assignee: ROHR, INC.
    Inventor: Norman John James
  • Patent number: 9784214
    Abstract: Aspects are directed to a system that includes an outer structure of a thrust reverser, a blocker door, and a plurality of four-bar mechanisms arranged in series with one another that couple the outer structure and the blocker door. Aspects are directed to a system for a thrust reverser of an aircraft that includes a blocker door, a kinematic mechanism configured to actuate the blocker door, and a pressure shelf, where the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, and where at least a portion of the kinematic mechanism is configured to reside above the pressure shelf.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: October 10, 2017
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 9784213
    Abstract: A blocker door for a gas turbine engine thrust reverser having a tray with a base and sidewalls extending about the base to define a volume, the volume being closed by a cover that extends beyond the periphery of the tray. The extension of the cover beyond the periphery provides a sealing feature.
    Type: Grant
    Filed: October 22, 2013
    Date of Patent: October 10, 2017
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag Todorovic
  • Patent number: 9783283
    Abstract: In order to limit the number of openings in an aircraft fuselage and to reduce the mass thereof, the invention makes provision for an item of aircraft fuselage equipment which is intended to be mounted in an opening of the fuselage, the item of equipment being configured to block/release an access passage which affords access to the inner side of the aircraft and which also comprises a discharge control valve for pressurization air.
    Type: Grant
    Filed: May 27, 2015
    Date of Patent: October 10, 2017
    Assignees: Airbus Operations SAS, Airbus SAS
    Inventors: Marc Tomasi, Patrick Lieven, Romain Delahaye, Matthieu De Kergommeaux, Laurent Lache, Didier Poirier
  • Patent number: 9771894
    Abstract: In various embodiments, a thrust reverser system may comprise a first cascade, a second cascade, an actuator, and a structural connecting member. The actuator may be radially disposed between the first cascade and the second cascade. The structural connecting member may be adjacent the actuator. The structural connecting member may be configured to structurally join the first cascade and the second cascade.
    Type: Grant
    Filed: April 8, 2015
    Date of Patent: September 26, 2017
    Assignee: Rohr, Inc.
    Inventors: Michael Ray Aten, Adam Stein
  • Patent number: 9765729
    Abstract: A fan ramp for use in a thrust reverser portion of a nacelle is disclosed. The nacelle is included in a propulsion system. The fan ramp extends circumferentially about an axial fan ramp centerline. The fan ramp includes a forward edge, an aft edge, and a first blocker door pocket. The forward edge is disposed proximate an aft end of a fan case. The fan case at least partially surrounds a fan section of a gas turbine engine. The aft edge is disposed proximate a forward end of an array of cascades. The array of cascades is operable to permit a bypass airstream to pass there through during a thrust reversing operation. The first blocker door pocket is operable to receive at least a portion of a forward edge of a first blocker door included in the nacelle.
    Type: Grant
    Filed: October 17, 2013
    Date of Patent: September 19, 2017
    Assignee: Rohr, Inc.
    Inventors: Michael Aten, Milan Mitrovic
  • Patent number: 9726110
    Abstract: An aircraft propulsion system may include a generally annular fan case defined by a fan configured to be disposed at a forward end thereof and a stator blade array configured to be disposed at an aft end thereof, a thrust reversing assembly comprising at least a portion of the fan case, the fan case comprising a generally annular cascade array, and/or a sleeve situated at least partially about the cascade array, the sleeve configured to deploy to expose the cascade array. The aircraft propulsion system may further comprise a blocker door coupled to at least one of the cascade array and an inner surface of the fan case, the blocker door configured to deploy to redirect airflow through the cascade array.
    Type: Grant
    Filed: November 26, 2013
    Date of Patent: August 8, 2017
    Assignee: ROHR, INC.
    Inventor: Norman J. James
  • Patent number: 9670875
    Abstract: Thrust reversers and methods to provide reverse thrust are disclosed. An example thrust reverser includes a cascade to direct air from an interior volume of an engine nacelle to generate reverse thrust with respect to a direction of travel, and an air extractor to extract a portion of air approaching the cascade from within the interior volume.
    Type: Grant
    Filed: October 31, 2012
    Date of Patent: June 6, 2017
    Assignee: The Boeing Company
    Inventors: Kurt Erik Acheson, Chen Chuck
  • Patent number: 9631578
    Abstract: A pivot thrust reverser includes a first pivot door forming a first portion of a nacelle when stowed and second pivot door forming a second portion of the nacelle when stowed. The first pivot door and second pivot door each form a portion of a surface of a bypass duct when in a stowed position. In the deployed position the first pivot door and the second pivot door circumferentially surround a portion of an inner surface of a bypass duct such that when the pivot thrust reverser is deployed during engine operation a fan bypass stream is redirected while both a core stream and a nacelle ventilation stream flow in substantially the same manner as when the pivot thrust reverser is stowed.
    Type: Grant
    Filed: February 19, 2014
    Date of Patent: April 25, 2017
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, T. David Bomzer
  • Patent number: 9617955
    Abstract: The present disclosure relates to a cascade thrust reverser providing that when a sliding cowl and a flap are in a direct jet position, a hook is held in engagement with another hook and the flap is immobilized inside of a housing of the sliding cowl by a stem of a telescopic connecting rod subjected to pre-stress generated by a compressed spring located in the body of the connecting rod. When the sliding cowl starts to slide from the direct jet position toward the reverse jet position, the hooks disengage each other and the stem engages with an extension in the body of the connecting rod, so that the flap is rotated from the direct jet position toward the reverse jet position due to the tensile force exerted by the stem.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: April 11, 2017
    Assignee: AIRCELLE
    Inventors: Vincent Peyron, Laurent Georges Valleroy, Franck Depoortere