With Means Controlling Amount, Shape Or Direction Of Discharge Stream Patents (Class 239/265.19)
  • Patent number: 11913406
    Abstract: A thrust reverser system is provided that includes a sleeve, a fixed cascade structure and a blocker door. The fixed cascade structure is within a cavity of the sleeve when the sleeve is in a sleeve stowed position. The blocker door is within the cavity of the sleeve when the sleeve is in the sleeve stowed position and the blocker door is in a blocker door stowed position. The blocker door projects in a radial inward direction away from the sleeve towards the centerline when the sleeve is in a sleeve deployed position and when the blocker door is in a blocker door deployed position. The blocker door includes a pivot attachment fixed at an end of the blocker door. The pivot attachment is configured to move in a forward direction from a first location to a second location.
    Type: Grant
    Filed: April 7, 2021
    Date of Patent: February 27, 2024
    Assignee: ROHR, INC.
    Inventor: Jai Ganesh Palanisamy
  • Patent number: 11885281
    Abstract: An aeronautical thrust reverser including a sliding cowl, shutter flaps and deflection cascades. The reverser includes, for each flap, a return member hinged to the sliding cowl, to a driving connecting rod itself hinged to a front frame of the reverser, and to a return connecting rod itself hinged to the flap, the latter being moreover hinged by its rear end to the sliding cowl. The return member, the driving connecting rod and the return connecting rod form an actuation system capable of opening the secondary flow duct in a direct thrust configuration.
    Type: Grant
    Filed: October 20, 2020
    Date of Patent: January 30, 2024
    Assignee: SAFRAN NACELLES
    Inventors: Josse Plaquin, Cedric François Pierre Renault
  • Patent number: 11879416
    Abstract: A method of thrust vectoring a missile utilizing jet tabs is presented. Jet tabs are used to create lateral control moments on a missile by rotating tabs into the rocket exhaust plume and changing the thrust deflection angle. The method includes simultaneously rolling the missile during the thrust vector maneuver in order to reduce the maximum tab exposure to the rocket plume. The method enables aggressive pitchover maneuvers while reducing the risk of tab failure due to excessive exposure.
    Type: Grant
    Filed: September 9, 2022
    Date of Patent: January 23, 2024
    Assignee: Raytheon Company
    Inventors: Brandon J. Napier, Scott R. Wells, Derek T. Betts, Kevin R. Albrecht
  • Patent number: 11733011
    Abstract: A power take-off (PTO) system includes a spur pinion on a shaft, used to turn a sector face gear that is coupled to a surface to be turned, such as a jet vane in a rocket nozzle. These may be parts of a thrust vectoring system, with the PTO system used to connect to a control surface actuator for a control surface such as a fin. The mechanical coupling between the fin and the jet vane may enable steering of a flight vehicle such as a missile at both low speeds and high speeds, with the thrust vectoring by the jet vane effective at low airspeeds and the control surface movement used for steering at high airspeeds. The PTO system may be backward compatible with prior systems, while allowing a more direct connection between the control surface actuator and the thrust vectoring system, with a reduced number of parts.
    Type: Grant
    Filed: November 24, 2020
    Date of Patent: August 22, 2023
    Assignee: Raytheon Company
    Inventor: John Bugge
  • Patent number: 11692509
    Abstract: A thrust reverser assembly may comprise a cascade of vanes and a sleeve configured to translate relative to the cascade of vanes. The sleeve may include an inner sleeve portion, an outer sleeve portion, and a pressure sleeve portion. The pressure sleeve portion may be located radially inward of the outer sleeve portion and may extend forward from the inner sleeve portion. A blocker door may be hingedly coupled to the pressure sleeve portion. A drag link may be pivotably coupled to the blocker door. A forward end of the drag link may be configured to deploy radially inward in response to aft translation of the sleeve.
    Type: Grant
    Filed: July 8, 2021
    Date of Patent: July 4, 2023
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 11566583
    Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a thrust reverser system. The thrust reverser system includes a cascade structure and a scoop. The cascade structure is configured with a plurality of flow passages. Each of the flow passages extends through the cascade structure. The flow passages include a first flow passage. The scoop is configured to direct fluid into at least the first flow passage. The scoop includes a serrated leading edge.
    Type: Grant
    Filed: February 9, 2022
    Date of Patent: January 31, 2023
    Assignee: Rohr, Inc.
    Inventors: Radhakrishna Chilukuri, Ashok Babu Saya, Hussain Mahamed Javed Tapadar
  • Patent number: 11435761
    Abstract: A system and method for distributed flight control configured for use in an electric vehicle wherein the system includes a flight control assembly which further includes at least a sensor electronically connected to the flight control assembly. The sensor is configured to capture at least an input datum, and at least a performance datum. The system further includes a plurality of modular flight controllers communicatively coupled to at least an actuator of a plurality of actuators, wherein each modular flight controller of the plurality of modular flight controllers is configured to the multitude of data from at least a sensor, generate an attitude control datum, determine at least an actuator instruction datum, and perform a control allocation configured for the at least a actuator from the plurality of actuators to follow as a function of the flight control assembly.
    Type: Grant
    Filed: July 23, 2021
    Date of Patent: September 6, 2022
    Assignee: BETA AIR, LLC
    Inventor: Herman Wiegman
  • Patent number: 11352150
    Abstract: A spacecraft structure for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.
    Type: Grant
    Filed: January 27, 2020
    Date of Patent: June 7, 2022
    Assignee: MOMENTUS SPACE LLC
    Inventors: Matthew Parman, Joel Sercel, Mikhail Kokorich, James Small, Nicholas Simon, Nathan Orr, Samuel Avery, Scott Stanley
  • Patent number: 11326551
    Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: May 10, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David L. Sutterfield, Jack D. Petty, Bryan H. Lerg, Andrew Sanderson
  • Patent number: 11274631
    Abstract: A variable exhaust nozzle for a gas turbine engine includes an outer shroud and an inner plug. The outer shroud is arranged circumferentially about an axis. The inner plug extends along the axis and is at least partially located within the outer shroud. At least one of the outer shroud and the inner plug are movable selectively to cause a variable area region of the variable exhaust nozzle to change.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: March 15, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Andrew Sanderson, David L. Sutterfield, Bryan H. Lerg
  • Patent number: 11248561
    Abstract: An exhaust nozzle of a gas turbine engine includes an outer nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. A first strut is connected to the wall by a first connection allowing movement of the strut relative to the nozzle wall in the axial direction. Another strut is connected to the wall by a second connection allowing movement of the strut relative to the wall in the radial and axial directions. The second connection is formed by a sliding element and a receiving slot, wherein the sliding element includes an interaction zone interacting with an actuator for axial movement. The interaction zone has a radial length such that the interaction between the actuator and the interaction zone is maintained when the sliding element is moved in the radial direction by radial thermal expansion of the strut and/or the centerbody.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: February 15, 2022
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Predrag Todorovic
  • Patent number: 11242821
    Abstract: A turbofan having a nacelle delimiting a duct for a bypass flow and including a fixed structure including a guide vane support with guide vanes, a mobile cowl movable in translation between an advanced position and a retracted position, arms, each one being mobile in rotation on the guide vane support between a stowed position and a deployed position and comprising a distal end and a proximal end, for each pair of adjacent arms, a flexible screen extending angularly between the two arms, and of which an exterior edge is attached to the guide vane support, and wherein the distal end of each arm is fixed along the interior edge, a link rod mounted articulated between the distal ends, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Such an arrangement allows a reduction in weight.
    Type: Grant
    Filed: January 4, 2021
    Date of Patent: February 8, 2022
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Lionel Czapla, Benjamin Thubert, Julien Le Fanic
  • Patent number: 11215141
    Abstract: A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.
    Type: Grant
    Filed: June 4, 2019
    Date of Patent: January 4, 2022
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Pascal Gardes, Frédéric Ridray, Lionel Czapla
  • Patent number: 11203999
    Abstract: The present disclosure relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle. The hydraulic control system includes devices for actuating and controlling the reverser having hydraulic locks and cylinders, the corresponding hydraulic solenoid valves, and sensors. The turbofan includes a full-authority electronic computer or aircraft having an avionics computer that gives reverse thrust commands. The system further includes an electronic concentration module, different from the computer, which concentrates the data relating to the operation of the reverser actuation and control devices. The module includes internal contact switches for controlling the solenoid valves, a device for monitoring the sensors, a device for analog or digital processing of the data, and a bus for communication with the computer.
    Type: Grant
    Filed: June 14, 2018
    Date of Patent: December 21, 2021
    Assignee: Safran Nacelles
    Inventor: Vincent Pierre Germain Le Coq
  • Patent number: 11204183
    Abstract: The present invention discloses a ventilator with dual flow passages. There is a mode switcher on the partition board. The ventilator has a variety of operating modes, such as, the natural or mechanical driving mode according to outdoor wind speed, and single-effect or multi-effect filtration according to the outdoor air pollution conditions. The single-effect filtration uses only the primary-efficiency filter, while the three-effect filtration uses the primary-, medium-, and high-efficiency filters. The mode switcher on the partition board can open or close the by-pass baffle to bypass or go through the medium- and high-efficiency filters for switching between the single-effect and multi-effect filtration. In case some indoor pollution sources need to be removed quickly, the recirculated indoor air filtration can be run. In such situation, the primary-efficiency filter in the mechanically-driven flow passage is bypassed, while the fan drives indoor air passing the medium- and high-efficiency filters.
    Type: Grant
    Filed: May 28, 2018
    Date of Patent: December 21, 2021
    Assignee: DALIAN UNIVERSITY OF TECHNOLOGY
    Inventors: Tengfei Zhang, Facheng Li, Jihong Wang, Shugang Wang
  • Patent number: 11187190
    Abstract: A turbofan having a nacelle comprising a slider being mobile in translation between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one being mobile in rotation on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade. The maneuvering system comprises, for each blade, a shaft being mobile in rotation on the slider and on which the blade is fixed, a toothed sector being fixed to the shaft, a toothed arc being mobile in rotation on the slider, and having a bearing face, a threaded rod mounted fixed on the fixed structure, a cam having a tapped hole screwed onto the threaded rod and mounted fixed in translation with respect to the slider, and a return arrangement that presses the bearing face against the cam outer surface.
    Type: Grant
    Filed: July 13, 2020
    Date of Patent: November 30, 2021
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Laurent Cazeaux, Antoine Boudou
  • Patent number: 11187186
    Abstract: An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: November 30, 2021
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Predrag Todorovic, Thomas Schillinger
  • Patent number: 11092110
    Abstract: A rocket engine benefiting from better behavior during its starting stage, the rocket engine (1) including a diverging section (13) and a lashing system (40) configured to hold the diverging section (13) while starting the rocket engine (1), the lashing system (40) comprising: a plurality of radial cables (42) connected at respective first ends to a plurality of points of the diverging section (13), and a peripheral cable (41) connected to the second ends of the radial cables (42) and configured to co-operate with attachment points (43) of a launch platform (3).
    Type: Grant
    Filed: August 23, 2017
    Date of Patent: August 17, 2021
    Assignee: Arianegroup SAS
    Inventors: Alain Pyre, Gérard Roz
  • Patent number: 11066179
    Abstract: A seal assembly may comprise a door configured to translate relative to a static structure. A seal may be disposed in a seal envelope defined, at least, partially by the static structure and the door. The seal may be configured to compress in a direction generally perpendicular to a direction of motion of the door.
    Type: Grant
    Filed: September 9, 2019
    Date of Patent: July 20, 2021
    Assignee: Rohr, Inc
    Inventors: Jihad Ramlaoui, Timothy Slattery
  • Patent number: 10995701
    Abstract: A thrust reverser assembly may comprise a sleeve including an inner sleeve portion and an outer sleeve portion. A plurality of guide rails may be coupled to a radially outward surface of the inner sleeve portion. A plurality of blocker doors may be slidably coupled to the plurality of guide rails. The plurality of blocker doors may be located between the inner sleeve portion and the outer sleeve portion.
    Type: Grant
    Filed: October 28, 2019
    Date of Patent: May 4, 2021
    Assignee: Rohr, Inc.
    Inventors: Jai Ganesh Palanisamy, Boopathy Saravanan
  • Patent number: 10975804
    Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: April 13, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: John R. Buey, Robert H. Bush, Felix Izquierdo
  • Patent number: 10961951
    Abstract: Disclosed is a thrust reverser for a device receiving a propulsion element, such as a turbojet engine nacelle. The thrust reverser includes a stationary structure having a deflector deflecting at least a portion of the air flow that is to flow through the nacelle, a translatably movable cap that can be in a closed position in which the cap covers the deflector deflecting the air flow and an open position in which the cap opens the deflector deflecting the air flow, and at least one moving actuator configured to move the cap between the open and closed positions. The moving actuator includes a stationary portion designed to be attached to the stationary structure in a first securing position and a movable portion designed to be attached to the cap in a second securing position. An adjusting device adjusts the first securing position.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: March 30, 2021
    Assignee: SAFRAN NACELLES
    Inventors: Alexis Tabouret, Alexis Loncle
  • Patent number: 10947929
    Abstract: An integrated propulsion system comprising at least two gas turbine engines, at least one fan, and a transmission assembly coupling the at least two gas turbine engines to the at least one fan wherein the at least two gas turbine engines are disposed within a main body of an airframe comprising the main body and a pair of wings, and wherein the number of gas turbine engines is greater than the number of fans.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: March 16, 2021
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventors: Edward C. Rice, Richard K. Keller, William B. Bryan
  • Patent number: 10907577
    Abstract: A lock mechanism for releasably securing a pivot door of a thrust reverser includes a frame, a blade housing connected to the frame, a blade member slidably disposed within the blade housing and configured to engage a lock fitting of the pivot door, an actuator configured to translate the blade member in a first direction with respect to the frame; a spring element configured to translate the blade member in a second direction with respect to the frame, and a loose-joint coupling configured to connect the actuator to the blade member.
    Type: Grant
    Filed: July 6, 2018
    Date of Patent: February 2, 2021
    Assignee: Rohr, Inc.
    Inventors: Imad D. Ghandour, Ken V. Huynh
  • Patent number: 10859035
    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: September 10, 2019
    Date of Patent: December 8, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Danis Burton Smith, Patrick S. Mulloy, Shawn Alstad
  • Patent number: 10850830
    Abstract: An aircraft includes a fuselage having a wing profile. An apparatus for thrust reversal is disposed on the tail of the aircraft. Air feed takes place from the outside, by way of a braking flap with an air intake channel and/or from a propelling machine.
    Type: Grant
    Filed: November 8, 2018
    Date of Patent: December 1, 2020
    Inventor: Dieter Lang
  • Patent number: 10822113
    Abstract: Sensor data is received from an inertial measurement unit on a vehicle. An observed attitude and an observed attitude rate of the vehicle are determined based on the sensor data. Using a model associated with a vehicle failure mode, an expected attitude and an expected attitude rate of the vehicle are determined. A malfunctioning rotor is determined based on the observed attitude, the observed attitude rate, the expected attitude, and the expected attitude rate. In response to identifying the malfunctioning rotor, a responsive action is performed, including by updating a geometry matrix so that at least one non-malfunctioning rotor in the plurality of rotors compensates for the malfunctioning rotor.
    Type: Grant
    Filed: September 10, 2018
    Date of Patent: November 3, 2020
    Assignee: Kitty Hawk Corporation
    Inventor: Mark Johnson Cutler
  • Patent number: 10738740
    Abstract: Provided is a thrust control apparatus having a plug area variable spike pintle nozzle, in which an aerospike-shaped pintle can be used in a pintle nozzle for precise thrust control. The thrust control apparatus includes a combustion chamber, a motor housing, and an outer pintle nozzle. The motor housing has a driving motor within the combustion chamber. The outer pintle nozzle is moved in a lateral direction by the driving motor.
    Type: Grant
    Filed: January 24, 2020
    Date of Patent: August 11, 2020
    Assignee: AGENCY FOR DEFENSE DEVELOPMENT
    Inventors: Jun-Young Heo, Jeong-Jin Kim, Seok-Jin Oh
  • Patent number: 10731602
    Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.
    Type: Grant
    Filed: June 6, 2018
    Date of Patent: August 4, 2020
    Assignee: Airbus Operations S.A.S.
    Inventor: Olivier Pautis
  • Patent number: 10723054
    Abstract: Methods of fabricating a component, such as a cascade grid panel for a jet engine thrust reverser, having a plurality of cavities extending through the component, with each cavity having at least one surface with a complex contour, and related devices. A plurality of two or more mold inserts are stacked to form a mold insert stack, with the mold insert stack having a plurality of mold bosses formed by mold boss sets. The mold boss sets are each formed by a mold boss segment from each of the mold inserts. Further, the mold boss segments are affixed to respective baseplates so that the mold boss segments can be handled as a group and remain properly positioned relative to their neighboring mold boss segments.
    Type: Grant
    Filed: December 11, 2017
    Date of Patent: July 28, 2020
    Assignee: The Boeing Company
    Inventors: Chen Chuck, Everette D. Gray, David J. Barene, Tunde A. Olaniyan, Zachariah B. Vandemark
  • 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: 10598047
    Abstract: A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes an auxiliary electric motor control operable to control the core turning motor to drive rotation of the engine core using electric power while a full authority digital engine control that controls operation of the gas turbine engine is either depowered or in a power state that is less than a power level used by the full authority digital engine control in flight operation.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jesse W. Clauson, Frederick M. Schwarz
  • Patent number: 10563620
    Abstract: An expandable exhaust cone assembly is described which is able to move from a collapsed position to an expanded position.
    Type: Grant
    Filed: August 12, 2016
    Date of Patent: February 18, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Douglas D. Dierksmeier, Edward C. Rice, Ryan C. Humes
  • Patent number: 10519898
    Abstract: A linkage comprises a drive ring, a flap linkage mounted to each of a multiple of flaps and the drive ring, and an actuator system which drives the drive ring to cause the multiple of flaps to pivot. A method of driving a multiple of flaps is also disclosed.
    Type: Grant
    Filed: August 26, 2015
    Date of Patent: December 31, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Robert L. Gukeisen
  • Patent number: 10428764
    Abstract: A cascade assembly of a nacelle for a turbofan engine includes a cascade concentrically disposed about an centerline, and a translating sleeve constructed and arranged to move between a forward position and an aft position along the centerline. A deflection limiter of the cascade assembly includes a first surface facing at least in-part in a radial direction and a second surface facing at least in-part in an opposite radial direction. The first surface is carried by one of the cascade and the translating sleeve and the second surface is carried by the other of the cascade and the translating sleeve. The first and second surfaces oppose one-another for limiting deflection when the translating sleeve is in the aft position and are spaced axially apart when the translating sleeve is in the forward position.
    Type: Grant
    Filed: February 10, 2016
    Date of Patent: October 1, 2019
    Assignee: ROHR, INC.
    Inventor: Sara Christine Crawford
  • Patent number: 10385805
    Abstract: A variable geometry exhaust nozzle arrangement includes a plurality of hingable exhaust petals defining a perimeter of an exhaust duct and an annular ring slidably engagable against a radially outer surface of each petal. The annular ring is coupled to a plurality of circumferentially spaced actuator arrangements, each including first and second circumferentially spaced parallel actuator arms pivotably coupled to the annular ring at a first end and to a slide arrangement at a second end. Each slide arrangement is mounted for linear sliding movement relative to the annular ring, such that sliding movement of each slide arrangement causes pivoting of the first and second actuator arms to thereby translate the annular ring in one or both of a longitudinal direction and a lateral direction.
    Type: Grant
    Filed: October 4, 2017
    Date of Patent: August 20, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Jack F Colebrooke
  • Patent number: 10378480
    Abstract: A thrust reverser blocker door may comprise a proximal surface, a distal surface located opposite the proximal surface, a first attachment feature extending from the distal surface, a second attachment feature extending from the distal surface, a drag link housing extending from the distal surface, a first diagonal stiffener extending from the distal surface and extending between the first attachment feature and the drag link housing, a second diagonal stiffener extending from the distal surface and extending between the second attachment feature and the drag link housing, a first perimetrical stiffener extending from the distal surface and extending from the first attachment feature and the drag link housing, a second perimetrical stiffener extending from the distal surface and extending from the second attachment feature and the drag link housing, and a middle stiffener extending between the first attachment feature and the second attachment feature.
    Type: Grant
    Filed: February 10, 2017
    Date of Patent: August 13, 2019
    Assignee: Rohr, Inc
    Inventors: Adrian A Gutierrez, Isaac N Wanjohi
  • Patent number: 10352273
    Abstract: A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.
    Type: Grant
    Filed: November 8, 2016
    Date of Patent: July 16, 2019
    Assignee: Rohr, Inc.
    Inventors: Christian Soria, Charles M. Biset, Andrew S. Gurney
  • Patent number: 10309315
    Abstract: An example turbofan engine starting system includes a core nacelle housing a compressor and a turbine. The core nacelle is disposed within a fan nacelle. The fan nacelle includes a turbofan. A bypass flow path downstream from the turbofan is arranged between the two nacelles. A controller is programmed to manipulate the nozzle exit area to facilitate startup of the engine. In one example, manipulates the nozzle exit area using nozzles, in response to an engine shutdown condition. The nozzles open and close to adjust the nozzle exit area.
    Type: Grant
    Filed: March 29, 2016
    Date of Patent: June 4, 2019
    Assignee: United Technologies Corporation
    Inventors: Ashok K. Jain, Michael Winter
  • Patent number: 10273904
    Abstract: The invention relates to a fairing (37) for a mixer (28) of a nozzle (26) of a dual-flow turbomachine (20), said mixer being of an overall annular shape and extending along a longitudinal axis (24) of the turbomachine, said mixer comprising an upstream part (29) provided with a flange (31) extending radially toward the outside of the mixer, intended to be fastened to an exhaust casing (21) of the turbomachine, and a downstream part (33) forming a flow mixing area, the fairing (37) being of an overall annular shape and configured to extend around the upstream part (29) of the mixer (28) and to be attached to the flange (31) of said upstream part (29), the fairing being without means for fastening to the downstream part (33) of the mixer (28), in such a way as to connect the fairing (37) to the mixer (28) at a distance from the flow mixing area.
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: April 30, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benoit Argemiro Matthieu Debray, Mario Cesar De Sousa, Gregory Ghosarossian-Prillieux, Frederic Noel
  • Patent number: 10215094
    Abstract: A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.
    Type: Grant
    Filed: August 7, 2015
    Date of Patent: February 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Karl L. Hasel
  • Patent number: 10180117
    Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.
    Type: Grant
    Filed: August 5, 2016
    Date of Patent: January 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, T. David Bomzer
  • Patent number: 10167815
    Abstract: A thrust reverser of a turbofan pod is provided that includes movable cowlings that retract relative to stationary front structure to reveal stationary or movable thrust reverser cascades, as well as a secondary variable nozzle section connected to the movable cowlings by guiding means enabling movement controlled by actuators engaged with the front structure to apply an axial thrust. The actuators are directly connected to the secondary nozzle, and in that the thrust reverser comprises latches connected to the movable cowlings, having two positions providing, alternately, latching onto the front structure or latching onto the control of the secondary nozzle.
    Type: Grant
    Filed: October 11, 2016
    Date of Patent: January 1, 2019
    Assignee: AIRCELLE
    Inventors: Patrick Boileau, Olivier Kerbler
  • Patent number: 10161357
    Abstract: A thrust reverser track beam may comprise a noise suppressing structure. The noise suppressing structure may form the airflow surface of the track beam. The noise suppressing structure may be riveted, bolted, or bonded to the track beam.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: December 25, 2018
    Assignee: ROHR, INC.
    Inventor: Jacques Lu
  • Patent number: 10151270
    Abstract: An engine cowling of an aircraft gas-turbine engine with a thrust-reversing device, with a core engine and a bypass duct surrounding the latter, and with a front cowling enclosing the bypass duct and a rear cowling movable in the axial direction, as well as with cascade elements arranged over the circumference which can be placed by a substantially axial movement into an intermediate space resulting from a movement of the rear cowling relative to the front cowling, characterized in that the cascade elements are connected directly to the rear cowling, that the rear cowling has a rounded outer leading edge and that the cascade element has at its rear area a flow-guiding element, in front of which several thrust-reversing stator vanes are arranged and behind which at least one flow stator vane is arranged whose curvature shape matches the rounding of the outer leading edge of the rear cowling.
    Type: Grant
    Filed: February 18, 2016
    Date of Patent: December 11, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Predrag Todorovic, Carlos Omar Marquez Gutierrez, Gero Schieffer
  • Patent number: 10087884
    Abstract: Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing.
    Type: Grant
    Filed: October 7, 2015
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Donald W. Peters, James P. Bangerter
  • Patent number: 10077739
    Abstract: A cascade-variable area fan nozzle system (the “CVAFN System”) is provided. The CVAFN system may comprise a cascade portion and a variable area fan nozzle (“VAFN”) portion. The VAFN portion may include a VAFN panel. The cascade and VAFN panel may be integrally formed with one another. The CVAFN system may include an actuation system (e.g., a jack screw) that is configured to translate the cascade and VAFN panel forward and aft. The cascade and VAFN panel may be translated aft in response to activation of the thrust reverser and/or CVAFN system.
    Type: Grant
    Filed: April 24, 2014
    Date of Patent: September 18, 2018
    Assignee: ROHR, INC.
    Inventor: Norman J. James
  • Patent number: 10077669
    Abstract: A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: September 18, 2018
    Assignee: United Technologies Corporation
    Inventor: Anthony R. Bifulco
  • Patent number: 10066547
    Abstract: A drive architecture comprises a rotor and a gearbox for driving the rotor. A pair of input gears provides rotational drive to the gearbox. A first recuperative cycle engine drives one of the pair of gears and a second engine drives the other of the pair of gears. The first recuperative cycle engine and the second engine are both gas turbine engines. A power takeoff from a drive shaft of the second engine supplies rotational drive to drive at least one component in the first recuperative cycle drive.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: September 4, 2018
    Assignee: United Technologies Corporation
    Inventor: Daniel Bernard Kupratis
  • Patent number: 10060295
    Abstract: A method of working a non-conforming exhaust sleeve utilizes a first plate disposed over an outer surface of an exhaust sleeve and a second plate disposed over an inner surface. The exhaust sleeve includes an aft sleeve attached to an aft edge of a cellular layer and the first plate extends from the cellular layer onto the aft sleeve. The second plate is disposed along the inner surface of the cellular layer. A first plurality of fasteners secures the first plate to the second plate through the cellular layer and a second plurality of fasteners secures the first plate to the aft sleeve.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: August 28, 2018
    Assignee: United Technologies Corporation
    Inventor: Brian Kenneth Holland