Auxiliary Patents (Class 244/58)
  • Patent number: 10954865
    Abstract: Pressurized air systems for aircraft and related methods are described herein. An example pressurized air system includes a compressor having a compressor inlet and a compressor outlet. The compressor inlet receives air from a first air source and the compressor outlet supplies pressurized air to an environmental control system (ECS). The pressurized air system includes a turbine having a turbine inlet to receive air from a second air source, a first overrunning clutch operatively coupled between an output shaft of an accessory gearbox and the compressor, the accessory gearbox operatively coupled to a drive shaft extending from an engine of the aircraft, and a second overrunning clutch operatively coupled between the compressor and the turbine. The first and second overrunning clutches enable the accessory gearbox to drive the compressor during a first mode of operation and enable the turbine to drive the compressor during a second mode of operation.
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: March 23, 2021
    Assignee: The Boeing Company
    Inventor: Steve G. Mackin
  • Patent number: 10934013
    Abstract: Aircraft fuselage apparatus having embedded structural batteries are disclosed. An example apparatus includes a fuselage having a wall. The wall has an outer surface, an inner surface, and a structural battery embedded in the wall between the outer surface and the inner surface.
    Type: Grant
    Filed: September 22, 2017
    Date of Patent: March 2, 2021
    Assignee: THE BOEING COMPANY
    Inventor: Christopher C. Veto
  • Patent number: 10916969
    Abstract: Aspects of the subject disclosure may include, for example, obtaining power, by a communication device, from a current passing through a transmission medium via an inductive coupling between the communication device and the transmission medium where the communication device is physically connected with the transmission medium and providing communications, by the communication device, by electromagnetic waves that propagate without utilizing an electrical return path, wherein the electromagnetic waves are guided by one of the transmission medium or a dielectric core of a cable coupled to a feed point of a dielectric antenna. Other embodiments are disclosed.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: February 9, 2021
    Assignee: AT&T Intellectual Property I, L.P.
    Inventors: David M. Britz, Robert Bennett, Paul Shala Henry, Irwin Gerszberg, Farhad Barzegar, Thomas M. Willis, III, Donald J. Barnickel, Pamela A. M. Bogdan, Brandon Pimm, Ken Liu, Dorothy Zarsky, James Gordon Beattie, Jr.
  • Patent number: 10830210
    Abstract: An emergency wind turbine system for an aircraft including an outer structure in which an opening is made includes an emergency wind turbine including: a mast; a turbine including a body mounted on the mast that rotates about an axis of rotation, and a single blade or two blades extending radially from the body between a blade root and a blade head; a locking device to lock rotation of the turbine body about the axis of rotation, when the emergency wind turbine moves between retracted and deployed positions, such that the blade root axis forms an acute locking angle with an orthogonal projection of the longitudinal axis of the mast over a plane substantially perpendicular to the axis of rotation of the turbine and in which the blade root axis extends, to reduce the volume swept by the turbine when it moves between the retracted and deployed positions.
    Type: Grant
    Filed: December 7, 2016
    Date of Patent: November 10, 2020
    Assignee: Safran Electrical & Power
    Inventors: Eric Joseph Etienne Polin, Julien Guiraud
  • Patent number: 10793284
    Abstract: A multimode clutch assembly is positioned in a powertrain of a rotorcraft. The multimode clutch assembly includes a freewheeling unit having input and output races. The freewheeling unit has a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. A hydraulic actuator shifts the bypass assembly between the engaged position and a disengaged position. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the multimode clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the multimode clutch assembly is configured for bidirectional torque transfer.
    Type: Grant
    Filed: September 11, 2019
    Date of Patent: October 6, 2020
    Assignee: Bell Textron Inc.
    Inventors: David Andrew Prater, Eric Stephen Olson
  • Patent number: 10787274
    Abstract: A ram air turbine system includes a ram air turbine and an actuator to move the ram air turbine between a stowed position and a deployed position. The actuator is in fluid communication with an aircraft hydraulic system configured to return the ram air turbine to the stowed position from the deployed position during operation of the aircraft utilizing hydraulic fluid pressure from the aircraft hydraulic system. A method of operating a ram air turbine system includes slowing or stopping rotation of the ram air turbine during flight of the aircraft, directing hydraulic fluid pressure from an aircraft hydraulic system to a ram air turbine actuator to urge movement of the actuator from a deployed position to a stowed position and urging movement of the ram air turbine from a deployed position to a stowed position via movement of the actuator from the deployed position to the stowed position.
    Type: Grant
    Filed: August 16, 2016
    Date of Patent: September 29, 2020
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Michael E. Larson, Jr., Gary Sasscer, Scott J. Marks
  • Patent number: 10788088
    Abstract: A selectable clutch assembly for a multimode powertrain of a rotorcraft. The selectable clutch assembly includes a freewheeling unit having input and output sides. The freewheeling unit has a driving mode wherein torque applied to the input side is transferred to the output side and an over running mode wherein torque applied to the output side is not transferred to the input side. A bypass assembly is coupled to and rotatable with the output side of the freewheeling unit and is actuatable between engaged and disengaged positions with the input side of the freewheeling unit. In the disengaged position, the freewheeling unit is operable in the driving and the over running modes such that the selectable clutch assembly is configured for unidirectional torque transfer. In the engaged position, the over running mode of the freewheeling unit is disabled such that the selectable clutch assembly is configured for bidirectional torque transfer.
    Type: Grant
    Filed: February 13, 2019
    Date of Patent: September 29, 2020
    Assignee: Bell Textron Inc.
    Inventors: Eric Stephen Olson, Mark Alan Przybyla, David R. Bockmiller
  • Patent number: 10639956
    Abstract: Described in detail herein is an temperature-controlled UAV delivery system. One or more physical objects can be stored inside a temperature-controlled storage unit of a UAV. A temperature controlling device can control the temperature of the interior volume of the temperature-controlled storage unit. Sensors can detect a temperature of the interior volume of the temperature-controlled storage unit. The computing system can control the temperature controlling device to adjust the temperature of the interior volume of the temperature-controlled storage unit to an ideal temperature for storing the one or more physical objects based on the attributes associated with the one or more physical objects.
    Type: Grant
    Filed: January 29, 2018
    Date of Patent: May 5, 2020
    Assignee: Walmart Apollo, LLC
    Inventors: Robert Cantrell, David Winkle
  • Patent number: 10604233
    Abstract: A propeller for an aircraft having a fuselage and a pair of fixed wings includes a mounting member secured to at least one wing. At least one blade is rotatably connected to each mounting member and has an airfoil shape. The at least one blade is in a locked condition during take-off and landing of the aircraft extending parallel to a leading edge of the wing and in an unlocked, rotating condition during flight for propelling the aircraft.
    Type: Grant
    Filed: November 6, 2017
    Date of Patent: March 31, 2020
    Assignee: NORTHROP GRUMMAN SYSTEMS CORPORATION
    Inventor: Allen A. Arata
  • Patent number: 10590852
    Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, and a transmission transitionable between a first mode where an electric machine is driven at a first speed relative to the first towershaft, and a second mode where the electric machine is driven at a different, second speed relative to the first towershaft.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Hung Duong, Jonathan F. Zimmitti, William G. Sheridan, Michael E. McCune, Brian Merry
  • Patent number: 10590853
    Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, a hydraulic pump, and a transmission. The transmission is transitionable between a first mode where the hydraulic pump is driven at a first speed relative to a first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Hung Duong, Jonathan F. Zimmitti, William G. Sheridan, Michael E. McCune, Brian Merry
  • Patent number: 10553882
    Abstract: A fuel cell system includes a first fuel cell unit having a first fuel cell and a second fuel cell, a second fuel cell unit having a third fuel cell and a fourth fuel cell, a hydrogen tank coupled to all fuel cells, an oxygen supply unit and an air inlet. Oxidant inlets of the first fuel cell and the fourth fuel cell are couplable with the air inlet. Oxidant inlets of the second fuel cell and the third fuel cell are couplable with the oxidant supply unit couplable with at least one of the oxygen supply unit and the air inlet. Exhaust outlets of the first and fourth fuel cells are couplable with an inert gas outlet. Exhaust outlets of the second and third fuel cells are coupled with an exhaust switching unit couplable with the inert gas outlet and a water outlet.
    Type: Grant
    Filed: September 19, 2013
    Date of Patent: February 4, 2020
    Assignee: Airbus Operations GmbH
    Inventors: Ralf-Henning Stolte, Ralf Peck
  • Patent number: 10526976
    Abstract: A gas turbine engine comprises a high speed spool and a low speed spool. A low speed power takeoff is driven by the low speed spool and a high speed power takeoff is driven by the high speed spool. The low speed power takeoff drives a plurality of low speed driven accessories about low speed spool drive axes and the high speed power takeoff drives a plurality of high speed driven accessories about high speed spool drive axes. The low speed spool drive axes are generally tangential to an envelope defined about a center axis of the engine, and the high speed spool drive axes are generally tangential to an envelope defined about the center.
    Type: Grant
    Filed: April 27, 2017
    Date of Patent: January 7, 2020
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Hung Duong, Jonathan F. Zimmitti, William G. Sheridan, Michael E. McCune, Brian Merry
  • Patent number: 10487839
    Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally includes an electric machine rotatable with the rotary component and positioned coaxially with the rotary component at least partially inward of the core air flowpath. The electric machine is flexibly mounted to a static frame member, or flexibly coupled to the rotary component, or both, such that the electric machine is mechanically isolated or insulated from various internal and external forces on the gas turbine engine.
    Type: Grant
    Filed: August 22, 2016
    Date of Patent: November 26, 2019
    Assignee: General Electric Company
    Inventors: Thomas Kupiszewski, Brandon Wayne Miller, Daniel Alan Niergarth, Randy M. Vondrell, Paul Robert Gemin
  • Patent number: 10435166
    Abstract: An example cowling for a rotorcraft is hinged on a stationary part of an airframe of the rotorcraft and is pivotable from a closed position into a first partially open position and thereafter into a second fully open position. The example cowling includes a rod articulated on the cowling and having a free end configured to releasably engage with the airframe to hold the cowling in the first position; and at least one handhold attached to an exterior surface of the cowling, wherein the at least one handhold has a substantially straight section that in the fully open position rests on a top portion of the airframe so as to more evenly distribute the weight of the cowling on the airframe.
    Type: Grant
    Filed: May 17, 2017
    Date of Patent: October 8, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brent Scannell, Jean Pierre Paradis, Thomas Mast
  • Patent number: 10364037
    Abstract: The disclosure is directed to an optionally hybrid power system that may operate either as a traditional power system, deriving power from a single power source, or as a hybrid power system, deriving power from multiple types of power sources. An example optionally hybrid power system may include a gas turbine engine and one or more electric motors. When configured as a traditional power system the optionally hybrid power system may derive all power from the gas turbine engine. However, when configured as a hybrid power system, the one or more motors may be coupled to the optionally hybrid power system to supplement the power produced by the gas turbine engine. Additionally, an operator interface that may control the optionally hybrid power system may select from a plurality of operating modes that depend on the configuration of the optionally hybrid power system.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: July 30, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Michael James Armstrong, Richard K. Keller
  • Patent number: 10352416
    Abstract: An apparatus for unlocking an actuator comprises a first member mounted in a housing for rotation about an axis and having a circumferentially extending surface, a recess being formed in a section of the circumferentially extending surface. A second member for operative connection to a lock release element of an actuator is mounted for movement in a direction generally transverse to the axis of rotation of the first member and has a follower element resiliently biased into contact with the circumferentially extending surface of the first member. A rotary actuator is provided for rotating the first member about the axis between a first, locking position in which the follower element engages on the circumferentially extending surface and a second, unlocking position in which the follower element is at least partially received within the recess.
    Type: Grant
    Filed: June 29, 2016
    Date of Patent: July 16, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Daniel Trybula
  • Patent number: 10336461
    Abstract: An aircraft engine, an electric taxi system and a corresponding method are provided to facilitate taxiing without operation of the core gas turbine engine by driving the fan assembly with the electric taxi system during taxi operations. An aircraft engine is provided that includes a core gas turbine engine including a compressor, a combustor and a high pressure turbine. The aircraft engine also includes a fan assembly coupled to the core gas turbine engine. The aircraft engine further includes an electric taxi system coupled to the fan assembly. The electric taxi system includes an energy storage device and a motor responsive to energy provided by the energy storage device. The motor is coupled to the fan assembly and is configured to drive the fan assembly during taxi operations.
    Type: Grant
    Filed: January 5, 2016
    Date of Patent: July 2, 2019
    Assignee: THE BOEING COMPANY
    Inventor: Steve G. Mackin
  • Patent number: 10273823
    Abstract: An inlet door state control system for an auxiliary power unit (APU) includes an inlet door configured to allow air into an inlet of the APU. The system also includes an actuator configured to open the inlet door. The system also includes an APU threshold switch connected to the actuator, the APU threshold switch configured to automatically change from an open position to a closed position when a predetermined APU operating condition is met. In the system, the actuator opens the inlet door when the APU threshold switch is in the closed position.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: April 30, 2019
    Assignee: United Technologies Corporation
    Inventor: David C. Marcus
  • Patent number: 10267236
    Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component in communication with the mechanical component separated from the mechanical component by a firewall, the firewall comprising a first side and a second side, the second side having a lower operating temperature than the first side. A vibration isolation structure is located at the second side. The electronic module is connected thereto and includes at least one vibration isolator secured to the firewall to vibrationally isolate the electronic module from gas turbine engine vibrations.
    Type: Grant
    Filed: April 25, 2016
    Date of Patent: April 23, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Kurt J. Sobanski
  • Patent number: 10252810
    Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.01×RFP?0.311, such that the propulsion engine may operate at a desired efficiency.
    Type: Grant
    Filed: April 19, 2016
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Daniel Alan Niergarth, Randy M. Vondrell, Brandon Wayne Miller, Patrick Michael Marrinan
  • Patent number: 10093430
    Abstract: A mounting frame for a ram air turbine includes a front support block having a top side opposite a bottom side. A rear support block is disposed opposite the front support block, the rear support block also having a top side, and a bottom side. A top plate extends between the front support block and the rear support block, the top plate having a forward end connected to the front support block proximate the top side of the front support block, an aft end connected to the rear support block proximate the top side of the rear support block. A bottom plate extends between the front support and the rear support opposite the top plate.
    Type: Grant
    Filed: January 16, 2015
    Date of Patent: October 9, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: David Everett Russ, Kanthi Gnanam Kannan
  • Patent number: 10040561
    Abstract: Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a wind-powered aircraft includes an airframe suitable for untethered flight in an open airspace; and an airborne kinetic energy conversion system attached to the airframe, the airborne kinetic energy conversion system comprising a turbine, a generator connected to the turbine, and an electrical storage means connected to the generator.
    Type: Grant
    Filed: April 4, 2013
    Date of Patent: August 7, 2018
    Assignee: SUNLIGHT PHOTONICS INC.
    Inventors: Sergey V. Frolov, Michael Cyrus, Allan J. Bruce
  • Patent number: 10006476
    Abstract: An actuator assembly includes a housing, an internal cavity within the housing configured to partially contain a pressurized fluid, a fluid inlet port connecting a first opening on an outer surface of the housing to the internal cavity, a fluid outlet port connecting a second opening on the outer surface of the housing to the internal cavity, and a pressure relief channel having a relief inlet and a relief outlet. The relief outlet is in fluid communication with the internal cavity and a distance between the fluid inlet port and the relief outlet is less than half a distance between the fluid inlet port and fluid outlet port.
    Type: Grant
    Filed: May 22, 2015
    Date of Patent: June 26, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: David G. Bannon, Paul Michael Reinhard
  • Patent number: 9850820
    Abstract: A power transmission system for a turbine engine is provided. The power transmission system includes a transmission shaft that is connected to a drive shaft by bevel gears, and that drives equipment or accessories. The transmission shaft is designed to operate under supercritical conditions and includes a damper system for damping vibration at its resonant speed.
    Type: Grant
    Filed: October 3, 2014
    Date of Patent: December 26, 2017
    Assignees: SNECMA, HISPANO SUIZA
    Inventors: Serge Dominique Pettinotti, Vincent Abousleiman, Sebastien Bourget, Mickael Moreiras, Diane Gueudry, Bernard Cartier, Florian Poinsot-Berthelot
  • Patent number: 9664232
    Abstract: A generator assembly may include a bearing liner and a bearing retainer configured to reduce vibration response in a bearing assembly under high frequency operation of a rotor. The bearing liner may be configured to provide a clearance between the bearing assembly and an adjacent housing/bearing liner to prevent high vibration output from the bearing assembly on for example, the rotor shaft. The bearing retainer may include a recess to accommodate axial movement of the bearing assembly in response to rotation of the rotor. In some embodiments, the bearing retainer may include a dampener to dampen contact of the bearing assembly with the retainer.
    Type: Grant
    Filed: July 18, 2013
    Date of Patent: May 30, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Balwinder Singh Birdi, Simon Waddell, William Scherzinger, David Windish, Robert Cisneroz
  • Patent number: 9638105
    Abstract: A front-fan turbojet engine including at least one fluid circuit and an air/fluid heat exchanger by which the fluid is cooled by air external to the turbojet engine and a splitter for splitting a flow downstream of the fan between a primary flow and a secondary flow. The heat exchanger is associated with a thermoelectric generator including a first and a second thermal exchange surface, of which the first surface is in thermal contact with the airflow and the second surface is in thermal contact with the fluid to be cooled in the exchanger.
    Type: Grant
    Filed: April 22, 2013
    Date of Patent: May 2, 2017
    Assignees: LABINAL POWER SYSTEMS, SNECMA
    Inventors: Jean-Jacques Charrier, Moez Bensaied, Marc Missout, Francis Pottier, Stephane Ribeiro, Romain Tabart
  • Patent number: 9365295
    Abstract: A latch assembly for a RAT actuator includes a lever block having spaced apart first and second lateral walls interconnected to one another by a bridge wall. The first and second lateral walls provide a pivot axis at one end. A latch pin is at another end opposite the one end. The latch pin extends between the first and second lateral walls. A latch bearing is arranged in each of the first and second lateral walls. Each bearing receives an end of the latch pin and is configured to permit the latch pin to rotate relative to the lever block. A lever block is arranged within a housing and has first and second lateral walls interconnected to one another by a bridge wall. A solenoid is configured to push the lever block about the pivot axis during a deploy sequence.
    Type: Grant
    Filed: June 6, 2012
    Date of Patent: June 14, 2016
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Gary Sasscer, Richard Schweighart
  • Patent number: 9284062
    Abstract: A multi-zone battery station is provided, comprising a plurality of landing areas configured to support a UAV. The battery station may permit battery life to be reloaded onto a UAV, which may include recharging a battery of the UAV or exchanging the UAV battery for a new battery. The different zones may accommodate different UAV types, different battery types, or operate in accordance with different energy provision rules. A marker may be provided on a landing area to aid in guiding the UAV to an appropriate landing area.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: March 15, 2016
    Assignee: SZ DJI TECHNOLOGY CO., LTD
    Inventor: Mingyu Wang
  • Patent number: 9273610
    Abstract: A gas turbine engine includes a compressor, a combustor adjacent the compressor, a turbine adjacent the combustor, a shaft, a motor, a primary variable frequency drive, an auxiliary variable frequency drive, and an auxiliary motor. The motor is coupled to the shaft. The primary variable frequency drive is electrically connected to the motor and an AC power source. The auxiliary variable frequency drive is electrically connected to the primary frequency drive. The auxiliary motor is electrically connected to the auxiliary variable frequency drive.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: March 1, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: Daniel Fingleton, Rachel Bruno
  • Patent number: 9217417
    Abstract: A ram air turbine generator, for generating electrical power when the system is exposed to an airstream, includes a turbine having multiple blades and a rotor operably coupled to the blades and rotating about a shaft and stator mounted, such that rotation of the blades rotates the rotor, and the rotation of the rotor about the stator produces electrical power.
    Type: Grant
    Filed: October 31, 2012
    Date of Patent: December 22, 2015
    Assignee: GE AVIATION SYSTEMS LLC
    Inventors: Dinesh Nath Taneja, Paul James Wirsch, Jr.
  • Publication number: 20150122944
    Abstract: A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU unit, as an auxiliary engine, include a gas generator connected to, for the main engines, a reduction gearbox and an accessory gearbox for mechanical, electrical, and/or hydraulic power take-off and connected to, for the APU unit, at least one power conversion member. The power conversion member of the APU unit is connected to the equipment and accessories by the reduction gearbox and/or the accessory gearbox of the main engines.
    Type: Application
    Filed: June 12, 2013
    Publication date: May 7, 2015
    Applicants: TURBOMECA, MICROTURBO SA
    Inventors: Pascal Dauriac, Olivier Bedrine, Patrick Marconi, Jean-Francois Rideau
  • Publication number: 20150115099
    Abstract: An inlet door system includes a duct, an inlet door, and a plurality of openings. The duct is configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of an aircraft. The duct includes an inlet port, an outlet port, and a duct sidewall extending between the inlet port and the outlet port. The inlet door includes an inner surface, an outer surface, and an outer peripheral edge between the inner and outer surfaces. The door is rotationally coupled to the duct, and is configured to selectively rotate between a closed position and a plurality of open positions. The openings extend through the inlet door between the inner surface and outer surface, and each opening is disposed adjacent to the outer peripheral edge.
    Type: Application
    Filed: October 25, 2013
    Publication date: April 30, 2015
    Inventors: Murali Krishnan Payangapadan, Vunnam Kiran, Lavan Kumar Gundeti, Yogendra Yogi Sheoran, Bruce Dan Bouldin
  • Patent number: 9016068
    Abstract: A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. An oil system includes a first oil system component that houses oil. A first connector mechanically connects the first oil system component to the mid-turbine frame.
    Type: Grant
    Filed: July 13, 2012
    Date of Patent: April 28, 2015
    Assignee: United Technologies Corporation
    Inventors: Octavio Martin, Jorge I. Farah
  • Patent number: 8978352
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a windmill pump driven by a spool. A first pump driven by said spool with an air-oil cooler is located downstream of the first pump. A second pump is also driven the spool with an air-air precooler located downstream of the second pump. A method of operating a gas turbine engine during a “windmilling” condition includes driving a windmill pump with a spool during a “windmilling ” condition. A lubricant is communicated to a geared architecture with the windmill pump. A first pump is driven by the spool and an air-oil cooler is located downstream of the first pump.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 17, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Michael E. McCune
  • Patent number: 8978351
    Abstract: A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 17, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Allan R. Penda, Brian D. Merry, Jorn A. Glahn, Christoper M. Dye, Nathan Snape
  • Patent number: 8966876
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan, a geared architecture, a spool which drives the fan through the geared architecture, and at least one component geared to the spool and being operable to control a speed of the spool during a “windmilling” condition. A method of gas turbine engine operations during a “windmilling” condition is also disclosed.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Michael E. McCune
  • Patent number: 8966875
    Abstract: A gas turbine engine includes a constant speed transmission driven by a spool. The constant speed transmission drives a first pump and a second pump. In a further non-limiting example, the first pump is driven by a first drive shaft which is driven by the constant speed transmission and the second pump is driven by a second drive shaft which is driven by the first shaft through a gearbox to provide a constant speed ratio between the first shaft and the second shaft.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Allan R. Penda, Christopher M. Dye
  • Patent number: 8967531
    Abstract: A unique airborne electrical power and thermal management system and a unique aircraft having a unique airborne electrical power and thermal management system are provided. The electrical power and thermal management system includes a turbine, which may power loads, for example but not limited to, a generator and a refrigerant compressor. The turbine may be in fluid communication with a gas turbine engine bleed air source to extract power from bleed air for powering the loads. A combustor may be fluidly disposed between the bleed air source and the turbine. The turbine may be part of a gas turbine engine distinct from a propulsion gas turbine engine. In one aspect, at least a portion of the electrical power and thermal management system may be disposed within an aircraft external pod. The pod may be configured to appear similar to a conventional external fuel tank pod employed by the aircraft.
    Type: Grant
    Filed: March 28, 2012
    Date of Patent: March 3, 2015
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Steven Gagne, Rigoberto Rodriguez, William L. Siegel, John R. Arvin
  • Patent number: 8967530
    Abstract: A power generation system for integration into an aircraft system, including a secondary power supply device having a generator turbine arranged in a duct running between a forward opening and a rearward opening on the fuselage of the aircraft. An electromagnetic unlocking device locks and unlocks a covering device on the forward opening, depending on a signal strength supplied to the unlocking device. The system also includes an actuation device that generates an opening or closing signal for an opening and closing device, and an opening function switching device that activates the unlocking device electrically with a signal strength that locks the covering device in an initial state, and on receipt of a power requirement signal from a power generation monitoring device, activates the unlocking device with a second signal strength that unlocks the covering device.
    Type: Grant
    Filed: February 24, 2010
    Date of Patent: March 3, 2015
    Assignee: Airbus Operations GmbH
    Inventor: Sten Gatzke
  • Patent number: 8965659
    Abstract: A system of speed control for a ram air turbine of an aircraft includes a power electronics controller, at least one routing device in communication with the power electronics controller, at least one secondary load in serial communication with the at least one routing device and the power electronics controller, and a ram air turbine (RAT) in communication with the power electronics controller, wherein the power electronics controller is configured to apply the secondary load to the RAT through the at least one routing device in response to a transient speed increase of the RAT.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: February 24, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Dustin L. Kaap, Conor Riordan
  • Patent number: 8955809
    Abstract: A mount bracket for use in a cabin air supply system for an aircraft has three legs extending from a cylindrical central bore and at a first axial end of the bracket. There are two legs at an opposed second axial end. A central leg is on the first axial end, and two of the legs are positioned at each of two lateral sides at first and second ends. The legs extend to feet. Strengthening legs connect feet at each of the lateral sides, and to the central leg foot. A thickness of the strengthening legs connected to the central leg is defined as a first dimension. A distance along the first axial end between a laterally outermost portion of the feet at each of the lateral sides is defined as a second dimension. A ratio of the first dimension to the second dimension is between 0.032 and 0.037.
    Type: Grant
    Filed: December 5, 2012
    Date of Patent: February 17, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Mark Vignali, Brent J. Merritt
  • Patent number: 8950703
    Abstract: A method includes generating thrust at one or more engines of an aircraft. The method includes generating first electricity at a first power unit concurrently with generating second electricity at a second power unit. The first power unit and the second power unit are independent of the one or more engines of the aircraft. The first electricity has a first set of electrical characteristics and the second electricity has a second set of electrical characteristics, where the first set of electrical characteristics is different than the second set of electrical characteristics.
    Type: Grant
    Filed: October 17, 2013
    Date of Patent: February 10, 2015
    Assignee: The Boeing Company
    Inventors: Andrew J. Bayliss, John T. Paterson, Kevin Retz
  • Patent number: 8954206
    Abstract: The present disclosure relates to an unmanned aerial vehicle (UAV) able to harvest energy from updrafts and a method of enhancing operation of an unmanned aerial vehicle. The unmanned aerial vehicle with a gliding capability comprises a generator arranged to be driven by a rotor, and a battery, wherein the unmanned aerial vehicle can operate in an energy harvesting mode in which the motion of the unmanned aerial vehicle drives the rotor to rotate, the rotor drives the generator, and the generator charges the battery. In the energy harvesting mode regenerative braking of the generator reduces the forward speed of the unmanned aerial vehicle to generate electricity and prevent the unmanned aerial vehicle from flying above a predetermined altitude.
    Type: Grant
    Filed: February 14, 2013
    Date of Patent: February 10, 2015
    Assignee: The Boeing Company
    Inventor: Alfredo Criado
  • Patent number: 8950700
    Abstract: Apparatus and methods is used for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. A power take-off engages a rotor and is engaged in response to detecting a loss of engine power.
    Type: Grant
    Filed: October 27, 2011
    Date of Patent: February 10, 2015
    Assignee: Groen Brothers Aviation, Inc.
    Inventor: Jacob Johannes van der Westhuizen
  • Patent number: 8944367
    Abstract: A rotary wing aircraft propulsion system includes an engine, a heat exchanger cooling a fluid from the engine and a thermoelectric generator in thermal communication with the fluid to generate electrical power. The thermoelectric generator provides electrical power to at least one aircraft component.
    Type: Grant
    Filed: March 5, 2012
    Date of Patent: February 3, 2015
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Mark Denton Bystry, Jr., Joseph Simonetti, Matthew J. Tarascio, Michael Peter Strauss, Adam Kasprzyk, Timothy Fred Lauder
  • Patent number: 8939399
    Abstract: The present application relates to a regenerative or hybrid drive system for an aircraft. The drive system includes the use of a power augmentation device to selectively engage the drive system of an aircraft to store power. The power in the power augmentation device being configured to release a power burst to systems within the aircraft to perform critical flight maneuvers.
    Type: Grant
    Filed: July 31, 2012
    Date of Patent: January 27, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Areian Kouros, Roger Aubert, Paul Madej
  • Publication number: 20150014479
    Abstract: A method includes generating thrust at one or more engines of an aircraft. The method includes generating first electricity at a first power unit concurrently with generating second electricity at a second power unit. The first power unit and the second power unit are independent of the one or more engines of the aircraft. The first electricity has a first set of electrical characteristics and the second electricity has a second set of electrical characteristics, where the first set of electrical characteristics is different than the second set of electrical characteristics.
    Type: Application
    Filed: October 17, 2013
    Publication date: January 15, 2015
    Applicant: The Boeing Company
    Inventors: Andrew J. Bayliss, John T. Paterson, Kevin Retz
  • Patent number: 8931734
    Abstract: A ram air turbine assembly is provided including a release cable coupled at a first end to a turbine release pin and coupled at a second end to a release lever. Aluminum tubing surrounds a portion of the release cable. An upper cable bracket supports the aluminum tubing adjacent the first end of the release cable. A lower cable bracket supports the aluminum tubing adjacent the second end of the release cable. The lower cable bracket includes a threaded bushing having an axial bore for receiving the release cable. The threaded bushing is in direct contact with an end fitting coupled to the aluminum tubing.
    Type: Grant
    Filed: September 13, 2012
    Date of Patent: January 13, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: David Everett Russ, Kanthi Gnanam Kannan
  • Patent number: 8925865
    Abstract: An emergency supply system for a transportation means is provided. The system includes at least one fuel cell, a hydrogen tank, an oxygen tank, an extinguishing agent container, an oxidant supply unit and an extinguishing-agent supply unit. The oxidant supply unit includes an oxygen inlet connectable to the oxygen tank, an air inlet connectable to an air source, and an oxidant outlet connected to an oxidant inlet of the fuel cell. The oxidant supply unit either conveys oxygen from the oxygen inlet or air from the air inlet to the oxidant outlet. The extinguishing-agent supply unit includes a first extinguishing agent inlet connected to an exhaust air outlet of the fuel cell, a second extinguishing agent inlet connected to the extinguishing agent container, and an extinguishing agent outlet that is connectable to an extinguishing-agent inlet unit of at least one space of the transportation means.
    Type: Grant
    Filed: February 1, 2013
    Date of Patent: January 6, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Ralf-Henning Stolte, Gwenaelle Renouard Vallet, Paul Rohrbach, Rainer Beuermann