Patents Examined by Andrew H Nguyen
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Patent number: 11454194Abstract: A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.Type: GrantFiled: June 22, 2020Date of Patent: September 27, 2022Assignee: Safran NacellesInventors: Patrick Boileau, Pierre Caruel
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Patent number: 11448139Abstract: A valve assembly for a turbine engine includes a valve arranged in an air flow path. The valve has a shaft. The valve is movable between an open position and a closed position. A hydraulic actuator is coupled to the shaft. The hydraulic actuator is configured to utilize fuel as a working fluid. The hydraulic actuator is configured to move the valve between the open position and the closed position.Type: GrantFiled: May 24, 2019Date of Patent: September 20, 2022Assignee: Hamilton Sundstrand CorporationInventors: Francis P. Marocchini, Aaron F. Rickis, August M. Coretto, Scott W. Simpson, Gary R. Marconi, Glenn Gradischer
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Patent number: 11448138Abstract: A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.Type: GrantFiled: February 6, 2020Date of Patent: September 20, 2022Assignee: Raytheon Technologies CorporationInventors: Michael M. Romero, Gary Collopy
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Patent number: 11441514Abstract: The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus that includes a probe affixed to an aircraft engine frame and having a shaft having a barb at a first end and configurable to a first configuration and a second configuration, and a receiver affixed to a thrust reverser transcowl slider configured to accommodate the barb and having an end wall with an aperture defined therein, the aperture shaped to permit escapement of the barb in the first configuration and prevent escapement of the barb in the second configuration.Type: GrantFiled: October 2, 2018Date of Patent: September 13, 2022Assignee: Woodward, Inc.Inventors: Joseph Thomas Kopecek, Julian Sweet
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Patent number: 11441482Abstract: A translating inlet assembly may comprise a first inlet portion and a second portion configured to translate relative to the first portion. A track may be located in the first portion. A rail may be coupled to the second portion and configured to translate along the track. The rail and the track may form a load bearing component configured to transfer inertial loads experienced by the second portion. A first actuator may be operationally coupled to the rail and configured to drive the rail along the track.Type: GrantFiled: June 4, 2019Date of Patent: September 13, 2022Assignee: Rohr, Inc.Inventor: Anthony Lacko
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Patent number: 11434850Abstract: 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: GrantFiled: April 22, 2019Date of Patent: September 6, 2022Assignee: Rohr, Inc.Inventor: Timothy Gormley
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Patent number: 11434017Abstract: The invention relates to the field of fairings of aircraft propulsion units, and more particularly to an assembly comprising a longitudinal beam (31) configured to be mounted on a lateral of a turbofan (7) engine core (11), oriented parallel to a longitudinal axis (X) of the turbofan (7), an opening fairing (18) cowl (50) of the engine core (11) and a deployment mechanism (60) mounted on the longitudinal beam (31) to move the opening cowl (50) between an open position and a closed position.Type: GrantFiled: December 18, 2018Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Quentin Matthias Emmanuel Garnaud, Marc Patrick Tesniere
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Patent number: 11434848Abstract: A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.Type: GrantFiled: November 5, 2019Date of Patent: September 6, 2022Assignee: ROHR, INC.Inventor: Timothy Gormley
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Patent number: 11428190Abstract: A grid-type thrust reverser for a turbojet engine includes a moving O-shaped thrust reverser body that is generally cylindrical in shape around a longitudinal central axis (A) and includes an inner wall configured to delimit a cold air stream, with an inner structure that surrounds the turbojet engine, the movable thrust reverser body being mounted so as to be able to slide along the longitudinal central axis (A) between a direct jet position in which the outer cowl covers the thrust reverser grids, and a thrust-reversal position in which the outer cowl uncovers the thrust reverser grids. The movable thrust reverser body includes a first half-portion and a second half-portion that are mounted so as to each pivot about a longitudinal pivot axis (B), between a closed position and an open gullwing position for removing the turbojet engine, via the cradle.Type: GrantFiled: June 29, 2020Date of Patent: August 30, 2022Assignee: Safran NacellesInventors: Loïc Grall, Alexis Heau, Benjamin Brebion, Sébastien Michel Thierry Guillemant, Mélody Seriset, Patrick Boileau
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Patent number: 11414200Abstract: A nacelle may comprise an inlet and a fan cowl aft of the inlet. The fan cowl may include a fan cowl panel configured to rotate between an open position and a closed position. The nacelle may further comprise a securement retainer including a first portion coupled to an interior surface of the fan cowl panel and a second portion coupled to an aft inlet flange of the inlet. The first portion of the securement retainer may be configured to engage the second portion.Type: GrantFiled: June 18, 2019Date of Patent: August 16, 2022Assignee: Rohr, Inc.Inventors: Shashidhar Shivarudrappa, Rohit Kumar Sharma
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Patent number: 11401825Abstract: The invention regards a gas turbine engine control system and a method for limiting turbine overspeed in case of a shaft failure. The control system includes: an overspeed protection system that activates an activation member in case a shaft failure is detected; a fuel limiting mechanism coupled with the activation member, wherein the fuel limiting mechanism is configured to limit the fuel supply to the gas turbine engine combustor if the activation member is activated; a variable stator vane mechanism which is configured to adjust variable stator vanes of a compressor of the gas turbine engine in their rotational position, the variable stator vanes having a closed position which blocks air flow through the compressor.Type: GrantFiled: September 25, 2019Date of Patent: August 2, 2022Assignees: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, ROLLS-ROYCE PLCInventors: Jorge Calderon, David Brown
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Patent number: 11401889Abstract: A method of managing a gas turbine engine includes the steps of detecting an airspeed and detecting a fan speed. A parameter relationship is referenced related to a desired variable area fan nozzle position based upon at least airspeed and fan speed. The detected airspeed and detected fan speed is compared to the parameter relationship to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted in response to the determination of the target area fan nozzle position and at least one threshold.Type: GrantFiled: September 30, 2020Date of Patent: August 2, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Geoffrey T. Blackwell, William J. McVey, William G. Tempelman
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Patent number: 11401887Abstract: An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.Type: GrantFiled: July 16, 2020Date of Patent: August 2, 2022Assignee: Safran NacellesInventors: Patrick Gonidec, Olivier Kerbler, Alexandre Phi, Jean-Paul Rami, Stephane Tirel, Jean-Baptiste Goulard, Matthieu Vanderlinden, Arnaud Carles-Espiteau
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Patent number: 11391241Abstract: A nacelle system having a translating structure is disclosed. In various embodiments, the nacelle system includes a fixed structure; a thrust reverser having a translating sleeve configured to translate relative to the fixed structure and in response to a first dual-circuit hydraulic system; and a variable area fan nozzle having a translating nozzle configured to translate relative to the translating sleeve and in response to a second dual-circuit hydraulic system.Type: GrantFiled: August 5, 2019Date of Patent: July 19, 2022Assignee: Rohr, Inc.Inventor: Timothy Gormley
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Patent number: 11391242Abstract: A nacelle system having a translating structure is disclosed. In various embodiments, the system includes a fixed structure; a thrust reverser having a translating sleeve configured to translate relative to the fixed structure and in response to a first hydraulic system; and a variable area fan nozzle having a translating nozzle configured to translate relative to the translating sleeve and in response to a second hydraulic system. In various embodiments, the first hydraulic system and the second hydraulic system include a primary hydraulic actuator, the primary hydraulic actuator having a primary hydraulic fluid end and a primary gaseous fluid end; a secondary hydraulic actuator having a secondary hydraulic fluid end and a secondary gaseous fluid end; and a hydraulic supply line configured to fluidly couple the primary hydraulic fluid end of the primary hydraulic actuator to the secondary hydraulic fluid end of the secondary hydraulic actuator.Type: GrantFiled: August 5, 2019Date of Patent: July 19, 2022Assignee: Rohr, Inc.Inventor: Timothy Gormley
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Patent number: 11390394Abstract: A nacelle for an aircraft turbojet engine includes a thrust-reversing device with a fixed structure and a movable structure translatably movable along an axis substantially parallel with a longitudinal axis of the nacelle between a retracted position in which it provides aerodynamic continuity with the fixed structure of the nacelle during operation of the nacelle with forward thrust and a deployed position in which it opens a passage intended for the circulation of a diverted secondary air flow during operation of the nacelle with reverse thrust. The nacelle includes at least one position sensor configured and arranged in the nacelle for detecting a deformation of the movable structure exceeding a permitted predetermined deformation threshold.Type: GrantFiled: December 1, 2017Date of Patent: July 19, 2022Assignee: Safran NacellesInventors: Olivier Kerbler, Laurent Georges Valleroy, Corentin Hue, Alexis Heau
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Patent number: 11391243Abstract: Seals for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods are disclosed. A representative rocket propulsion system includes a rocket engine having an exhaust nozzle, a seal plate carried by the exhaust nozzle, and a seal engaged with the seal plate. The seal includes at least one support, multiple pivotable first flaps, carried by the at least one support and positioned to contact the seal plate, and multiple pivotable second flaps, with an individual second flap positioned to shield a corresponding individual first flap. At least one forcing element is operatively coupled to at least one of the individual first flap or the individual second flap, to apply a pivoting force to the at least one of the individual first flap or the individual second flap.Type: GrantFiled: March 9, 2020Date of Patent: July 19, 2022Assignee: Blue Origin, LLCInventors: Nathaniel Cantor, Colin Patterson, Adam Norman, Christopher P. Hupf
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Patent number: 11365692Abstract: A fuel metering circuit for a turbomachine includes: a meter; a pump; a control valve configured to return an excess flow of fuel delivered to the meter towards the pump on the basis of a fuel pressure differential at the terminals of the meter; a diaphragm; and a volumetric flow meter. The diaphragm and the volumetric flow meter are mounted parallel to the meter, downstream of the control valve, in order to determine a density of the fuel flowing in the metering circuit.Type: GrantFiled: July 13, 2018Date of Patent: June 21, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Loic Pora, Arnaud Bernard Clement Thomas Joudareff
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Patent number: 11346303Abstract: A thrust reverser actuation system includes a first cowl actuation system for translating a first cowl of a thrust reverser and a second, separate cowl actuation system for translating a second cowl of the thrust reverser. The system also includes a device operatively connected between the first cowl actuation system and the second cowl actuation system, and configured to transmit drive from one of the first and second cowl actuation systems to the other of the first and second cowl actuation systems in the event of a failure of the other of the first and second cowl actuation systems.Type: GrantFiled: May 9, 2019Date of Patent: May 31, 2022Assignee: GOODRICH ACTUATION SYSTEMS LIMITEDInventor: Antony Morgan
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Patent number: 11346304Abstract: A thrust reverser may include a frame, a track disposed on the frame, a carrier operatively coupled to the track, and a first reverser door operatively coupled to the carrier. The first reverser door is movable relative to the frame, wherein the first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction.Type: GrantFiled: September 4, 2019Date of Patent: May 31, 2022Assignee: ROHR, INC.Inventors: Timothy Gormley, Imad D. Ghandour