Starter Motor Mechanically Coupled To Power Plant Patents (Class 60/788)
  • Patent number: 12366208
    Abstract: A method and system used to control a rotational speed or a torque of an output drive shaft. The output drive shaft being coupled to a turbine engine. The turbine engine including an engine core and an engine starter assembly. The engine starter assembly including an air turbine starter, an output drive shaft and an electric motor.
    Type: Grant
    Filed: July 28, 2023
    Date of Patent: July 22, 2025
    Assignee: Unison Industries, LLC
    Inventors: Nagendra Baddam, Shiloh Montegomery Meyers, Brian Christopher Kemp, David Raju Yamarthi, Venkata Subramanya Sarma Devarakonda, David Allan Dranschack, Narendra Dev Mahadevaiah
  • Patent number: 12281582
    Abstract: An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.
    Type: Grant
    Filed: October 14, 2022
    Date of Patent: April 22, 2025
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Illya Emmanuel Arcos Perez, Ashish Rajput, Amarnath Kakarla, Narayanan Payyoor, Abhijeet Yadav, Abhishek Goverdhan, Balaraju Suresh, Ricardo Hernandez Pandeli, Suryarghya Chakrabarti, Nicholas M. Daggett, Gary W. Bryant
  • Patent number: 12264629
    Abstract: An air turbine starter with a housing; a turbine member located within the housing; a drive shaft operably coupled to the turbine member, and having an interior portion. The air turbine starter output shaft extending between a first end and a second end, the output shaft movable between a first position, where the first end is coupled to the engine, and a second position, where the second end is retained within the interior portion and the first end is uncoupled from the engine. A decoupler assembly is included for decoupling the output shaft from the engine.
    Type: Grant
    Filed: February 8, 2024
    Date of Patent: April 1, 2025
    Assignee: Unison Industries, LLC
    Inventors: Narendra Dev Mahadevaiah, Sharad Pundlik Patil, Pallavi Tripathi, Subrata Nayak, Milind Chandrakant Dhabade, Shiloh Montegomery Meyers, David Allan Dranschak
  • Patent number: 12253029
    Abstract: A system includes a main pump having a main pump shaft configured to connect to a gear box for driving the main pump with rotational power from the gear box in a run mode, and for driving the gear box with rotational power from the main pump in a start mode. The system includes a first fuel line with an inlet configured to connect to connected in fluid communication with a fuel source. The first fuel line includes a first branch in fluid communication with the main pump, and a second branch. A start pump is connected in fluid communication with the second branch of the first fuel line. A second fuel line connects the start pump in fluid communication with a pump management valve (PMV). A third fuel line connects the main pump in fluid communication with the pump management valve.
    Type: Grant
    Filed: August 7, 2023
    Date of Patent: March 18, 2025
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Eric Briggs, Naison E. Mastrocola
  • Patent number: 12209537
    Abstract: In accordance with at least one aspect of this disclosure, a system includes a fuel line, an electrically driven fuel pump configured to supply fuel to a first fuel line branch and a second fuel line branch, and a selector valve disposed in the fuel line at a juncture of a first fuel line branch and a second fuel line branch configured to communicate the electrically driven fuel pump with the first fuel line branch or the second fuel line branch based on a position of the selector valve. In a first position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the first fuel line branch to supply fuel to a combustor of the engine and drive a high pressure shaft at a first speed. In a second position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the second fuel line branch to drive a hydraulic rotation unit configured to drive the high pressure spool of the engine at a second speed different from the first speed.
    Type: Grant
    Filed: July 25, 2023
    Date of Patent: January 28, 2025
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Eric Briggs, Naison E. Mastrocola
  • Patent number: 12196137
    Abstract: A gas turbine engine includes a turbine section located at an engine central longitudinal axis, a combustor configured to drive rotation of the turbine with combustion products, and a compressor section coupled to the turbine section at the engine central longitudinal axis and driven by the turbine section. An auxiliary compressor is located fluidly between the compressor section and the combustor such that an airflow exiting the compressor section is directed toward the auxiliary compressor. The auxiliary compressor is driven independently from the compressor section and is configured to output the airflow toward the combustor.
    Type: Grant
    Filed: June 11, 2021
    Date of Patent: January 14, 2025
    Assignee: RTX CORPORATION
    Inventors: Neil Terwilliger, Lance L. Smith, Neal R. Herring, Christopher J. Hanlon
  • Patent number: 12173656
    Abstract: A turbine engine including an engine core, an engine drive shaft, an accessory gear box (AGB), an air turbine starter (ATS) and a bleed air circuit. The engine core has a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The engine drive shaft operably couples the fan section, the compressor section and the turbine section. The AGB and the ATS are operably coupled to the engine drive shaft.
    Type: Grant
    Filed: October 26, 2023
    Date of Patent: December 24, 2024
    Assignee: Unison Industries, LLC
    Inventors: Pallavi Tripathi, Sheo Narain Giri, Shiloh Montegomery Meyers, Brian Christopher Kemp
  • Patent number: 12084195
    Abstract: A dual drive, dual clutch accessory drive system for an aircraft including a first input shaft connected to a first pressure spool of a turbine engine. The first input shaft rotates at a first speed. A second input shaft is connected to a second spool of the turbine engine that is distinct from the first spool. The second input shaft rotates at a second speed. An output shaft operatively connected to an aircraft accessory. A first drive path selectively operatively connects the first input shaft with the output shaft. The first drive path includes a first clutch. The first drive path being operable to rotate the output shaft at the first speed. A second drive path operatively connects the second input shaft with the output shaft. The second drive path includes a second clutch. The second drive path is operable to rotate the output shaft at the second speed.
    Type: Grant
    Filed: July 16, 2021
    Date of Patent: September 10, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Aaron M. Finke, Michael R. Blewett
  • Patent number: 11988098
    Abstract: In a gas turbine engine of the type having a high-pressure (HP) spool and a low-pressure (LP) spool, methods of increasing surge margin and compression efficiency at a given thrust are provided. One method increases compression efficiency and includes transferring mechanical power from the HP spool to the LP spool to reduce a corrected speed of a HP compressor therein and raise a working line of a LP compressor therein. Another method increases surge margin and includes transferring mechanical power from the LP spool to the HP spool to increase a corrected speed of a HP compressor therein and lower a working line of a LP compressor therein.
    Type: Grant
    Filed: June 9, 2023
    Date of Patent: May 21, 2024
    Assignee: ROLLS-ROYCE plc
    Inventor: Caroline L Turner
  • Patent number: 11959589
    Abstract: An aircraft oil management system includes a generator, pump, and pump control system. The generator is mechanically coupled to a prime mover via a the rotor shaft and is configured to output three-phase power. The pump is mechanically decoupled from the rotor shaft and delivers oil to the generator. The pump control system drives the pump independent of a rotational speed of the rotor shaft.
    Type: Grant
    Filed: April 11, 2022
    Date of Patent: April 16, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Dhaval S. Patel, Aaron M. Finke, Glenn C. Lemmers, Jr., Andreas C. Koenig
  • Patent number: 11959387
    Abstract: An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support the drive shaft and the output shaft.
    Type: Grant
    Filed: April 26, 2023
    Date of Patent: April 16, 2024
    Assignees: Unison Industries, LLC, General Electric Company
    Inventors: Amit Arvind Kurvinkop, David Raju Yamarthi, David Allan Dranschak, Brian Christopher Kemp, Marc David Zinger, Parmeet Singh Chhabra, Roberto Karpik, Eliel Fresco Rodriguez
  • Patent number: 11815029
    Abstract: A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.
    Type: Grant
    Filed: August 23, 2022
    Date of Patent: November 14, 2023
    Assignee: Raytheon Technologies Corporation
    Inventor: Martin Richard Amari
  • Patent number: 11807378
    Abstract: A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine. A first controller is in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine.
    Type: Grant
    Filed: March 25, 2020
    Date of Patent: November 7, 2023
    Assignee: RTX CORPORATION
    Inventors: David Gelwan, Jesse W. Clauson, Frederick M. Schwarz
  • Patent number: 11795872
    Abstract: An engine system includes a gas turbine engine with a first compressor, a first combustor, and a first turbine. The engine system also includes a secondary power unit with a second compressor, a second combustor, a second turbine, a third compressor coupled to the second compressor, and an electric motor-generator, where the secondary power unit is coupled to the gas turbine engine. A controller is operable to determine an operating mode of the engine system, select an input energy source and an output type of the secondary power unit based on the operating mode, control the secondary power unit based on the input energy source and the output type as selected, detect a change in the operating mode of the engine system, and modify the input energy source and/or the output type of the secondary power unit based on the change in the operating mode.
    Type: Grant
    Filed: February 14, 2020
    Date of Patent: October 24, 2023
    Assignee: RTX CORPORATION
    Inventors: Andre M. Ajami, Ryan W. Hunter, Javier A. Cue
  • Patent number: 11767793
    Abstract: A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
    Type: Grant
    Filed: August 9, 2022
    Date of Patent: September 26, 2023
    Assignee: General Electric Company
    Inventors: Jeffrey Douglas Rambo, Gregory Michael Petrasko
  • Patent number: 11686313
    Abstract: Fluid pumping system for a vehicle with an internal combustion engine, the fluid pumping system comprising: a housing; an electric motor; a planetary gear with a first member that can be driven by the internal combustion engine, a second member driven by the electric motor, and a third member; and a pump driven by the third element of the planetary gear set, the housing being closed by a pump flange and a pulley with pulley cover, wherein at least the pulley and/or a ring gear disposed in the pulley is made of plastic.
    Type: Grant
    Filed: March 6, 2019
    Date of Patent: June 27, 2023
    Assignee: HANON SYSTEMS EFP DEUTSCHLAND GMBH
    Inventors: Christian Humer, Viktor Racz, Michael Wadsack
  • Patent number: 11668244
    Abstract: An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas and a gear train is drivingly coupled with the turbine member. A drive shaft is operably coupled with the gear train, and a decoupler is selectively coupled to the drive shaft for decoupling the air turbine starter from the engine.
    Type: Grant
    Filed: February 24, 2021
    Date of Patent: June 6, 2023
    Assignees: UNISON INDUSTRIES, LLC, GENERAL ELECTRIC COMPANY
    Inventors: Roberto Karpik, Subrata Nayak, David Allan Danschak, Shiloh Montegomery Meyers, Sharad Pundlik Patil, Eliel Fresco Rodriguez
  • Patent number: 11643980
    Abstract: A method of determining a calorific value of fuel supplied to a gas turbine engine of an aircraft comprises sensing at least one engine parameter during a first time period of aircraft operation during which the gas turbine engine uses the fuel; and, based on the at least one sensed engine parameter, determining a calorific value of the fuel. The sensing may be repeated such that the at least one engine parameter is monitored over time. The gas turbine engine may be a propulsive gas turbine engine of the aircraft or a gas turbine engine of an auxiliary power unit of the aircraft.
    Type: Grant
    Filed: June 29, 2022
    Date of Patent: May 9, 2023
    Assignee: ROLLS-ROYCE plc
    Inventors: Craig W Bemment, Benjamin J Keeler, Paul W Ferra, Alastair G Hobday, Kevin R McNally, Andrea Minelli, Martin K Yates
  • Patent number: 11572833
    Abstract: An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.
    Type: Grant
    Filed: April 2, 2019
    Date of Patent: February 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Elie Hellegouarch, Frédéric Paul Eichstadt, Quentin Matthias Emmanuel Garnaud
  • Patent number: 11542872
    Abstract: An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine having a low speed spool and a high speed spool, a generator operably coupled to the low speed spool, a high spool electric motor operably coupled to the high speed spool, and a controller. The controller is configured to control the hybrid gas turbine engine system in a powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust. The gas turbine engine transitions from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state.
    Type: Grant
    Filed: October 14, 2021
    Date of Patent: January 3, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Neil Terwilliger, John P. Virtue
  • Patent number: 11519552
    Abstract: A vehicle driveline component with a housing, a rotary power transmission system, a lubricant and a lubrication de-aerator. The housing defines a cavity and a sump. The rotary power transmission system is received in the cavity and includes a plurality of gears that are in meshing engagement. The lubricant is received in the sump and is employed to lubricate the rotary power transmission system. The lubrication de-aerator is received in the housing and has at least one matrix of de-aeration cells that extend between an upper surface and a lower surface. Each of the de-aeration cells has a cell inlet, which is formed through the upper surface, and a cell outlet that is formed through the lower surface. Each of the de-aeration cells tapers between its cell inlet and its cell outlet.
    Type: Grant
    Filed: April 21, 2022
    Date of Patent: December 6, 2022
    Assignee: American Axle & Manufacturing, Inc.
    Inventor: Jeffrey J. Ronning
  • Patent number: 11506208
    Abstract: A pump assembly for a motor vehicle, comprising at least one mechanical drive, at least one electric drive, and at least one planetary gearbox, wherein the mechanical drive and the electric drive are coupled to one another via the planetary gearbox, the electric drive comprising a rotor shaft that is designed as a hollow shaft, wherein the rotor shaft is mounted at one side on a housing of the pump assembly via a ball bearing and at the other side in a gear stage of the planetary gearbox.
    Type: Grant
    Filed: July 16, 2019
    Date of Patent: November 22, 2022
    Assignee: HANON SYSTEMS EFP DEUTSCHLAND GMBH
    Inventors: Michael Hofer, Christian Humer, Michael Wadsack, Viktor Racz
  • Patent number: 11492105
    Abstract: An arrowhead aircraft includes a pair of counter-rotating propellers, a jet engine module, and an exhausted module, wherein the counter-rotating propellers propel the aircraft but does not have angular momentum, and the exhausted module deployed around the exhausted end of the jet engine module, which reuses the waste heat from the exhausted end and reduces the noise. Wherein, the airflow system includes a shutter deployed at the bottom side of the body that controls the streamlines of airflow through the aircraft and a plurality of airfoils that will force the aircraft tilted to the desired direction. The present invention resolved the helicopter's vulnerabilities, such as its intricate mechanism, dragging response, dangers blades, hard to control angular momentum, high cost, and high training level.
    Type: Grant
    Filed: November 5, 2020
    Date of Patent: November 8, 2022
    Inventor: Rue-Lan Liang
  • Patent number: 11492976
    Abstract: A starter assembly includes a housing defining an interior, a rotatable pinion gear wherein the rotatable pinion gear extends exteriorly of the housing and operably coupling to a combustion engine, a torque sensor providing a torque output indicative of a torque experienced by the pinion gear, and a controller module configured operate a starting sequence for the starter assembly.
    Type: Grant
    Filed: January 6, 2021
    Date of Patent: November 8, 2022
    Assignee: GE Aviation Systems LLC
    Inventors: Ruben Blanco Aviles, Saul Ledesma
  • Patent number: 11465770
    Abstract: Disclosed is an air cycle machine (ACM) having: a turbine; a compressor; a compressor shaft connected to the compressor and configured to receive rotational energy from a gearbox; and a turbine shaft connected to the turbine and configured to provide rotational energy to the gearbox; wherein the turbine shaft and the compressor shaft operate at different rotational speeds.
    Type: Grant
    Filed: March 1, 2019
    Date of Patent: October 11, 2022
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Alan Retersdorf, Gregory L. DeFrancesco, Matthew Pess
  • Patent number: 11434824
    Abstract: A system for energy conversion is provided including a propulsion system, a fuel circuit, a combustion device and turbine separate from the propulsion system, and a load device. A fuel flow control device separates a flow of fuel from the fuel tank into a first portion of fuel and a second portion of fuel. A fuel circuit is configured to provide the first portion of fuel to a heat addition system at the propulsion system. A combustion device receives a flow of oxidizer from a compressor section of the propulsion system via a fluid circuit. The fuel circuit provides the second portion of fuel to the combustion device. The fluid circuit flows combustion gases to the turbine and the propulsion system. The load device is operably coupled to the turbine to receive an output torque via expansion of the combustion gases through the turbine.
    Type: Grant
    Filed: February 3, 2021
    Date of Patent: September 6, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jeffrey Douglas Rambo, Gregory Michael Petrasko
  • Patent number: 11408353
    Abstract: A gas turbine engine includes a plural spool assembly including a first spool and a second spool. The engine also includes an accessory configured to change between a motor mode and a generator mode and a transmission configured to transmit mechanical power between the accessory and at least one of the first spool and the second spool. The transmission, when the accessory is in the generator mode, is configured to transmit mechanical power from the first spool to the accessory for generating electric power at the accessory. The transmission, when the accessory is in the motor mode, is configured to transmit mechanical power from the accessory to the second spool.
    Type: Grant
    Filed: March 28, 2019
    Date of Patent: August 9, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: David K Jan, Christopher Zollars
  • Patent number: 11390169
    Abstract: Methods and systems are provided for controlling power generation in a vehicle. In one example, the vehicle includes a controller coupled to an auxiliary device through a communication link, the auxiliary device drawing power from a generator at a power interface. Power supplied to the auxiliary device is regulated by the controller through signals transmitted over the communication link.
    Type: Grant
    Filed: August 2, 2021
    Date of Patent: July 19, 2022
    Assignee: Ford Global Technologies, LLC
    Inventors: Stuart Salter, Ross Dykstra Pursifull, Paul Kenneth Dellock, David Brian Glickman, William Taylor
  • Patent number: 11391326
    Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.
    Type: Grant
    Filed: January 26, 2018
    Date of Patent: July 19, 2022
    Assignee: GE AVIO S.R.L.
    Inventors: Marco Garabello, Paolo Altamura, Gian Mario Bragallini, Alessio Gargioli, Jan Biskupski
  • Patent number: 11359546
    Abstract: Systems and methods to operate an engine in a bowed rotor mitigation mode. An engine starting system includes a starter coupled to the engine and with a compressor. A conduit system communicates a portion of the compressed air from the compressor to the starter. A load control valve controls compressed air from the compressor to the starter and to other loads. A starter air valve controls compressed air through the conduit system to the starter. At least one controller: receives a start signal from the engine; determines whether to initiate a bowed rotor mitigation of the engine; operates either the load control valve or the starter air valve to move to a predetermined static position; and operates the other of the load control valve or the starter air valve to achieve a target speed of the engine.
    Type: Grant
    Filed: April 20, 2020
    Date of Patent: June 14, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Cecilia Lam
  • Patent number: 11349264
    Abstract: A gas turbine engine includes a housing including a first component providing an AC signal into an input cable. The input cable extends to an input conductive plate. The input conductive plate is in contact with a dielectric plate, and an output conductive plate is attached to an opposed side of the dielectric plate. The output connective plate extends to an output cable extending to a second component, such that a capacitance based connection is provided between the input and output cables, to communicate from first component sensor to the second component.
    Type: Grant
    Filed: June 18, 2020
    Date of Patent: May 31, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Gurkan Gok, Joseph Zacchio, Goran Djuknic, Joseph V. Mantese, Brenda J. Lisitano, Jonathan Gilson, Coy Bruce Wood
  • Patent number: 11261795
    Abstract: A system for starting a turbine engine. The system may comprise a gearbox, a first starter, and a second starter. The gearbox may have a gearbox input shaft. The gearbox may be coupled to the turbine engine. The gearbox input shaft may be rotatively coupled to a spool of the turbine engine. The first starter may be coupled to the gearbox input shaft. The second starter may have a second-starter output shaft. The second-starter output shaft may be coaxial with the gearbox input shaft. The second starter may be coupled to the gearbox input shaft through the first starter.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: March 1, 2022
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: John Kusnierek, Matthew J. Starr
  • Patent number: 11110800
    Abstract: Methods and systems are provided for controlling power generation in a vehicle. In one example, the vehicle includes a controller coupled to an auxiliary device through a communication link, the auxiliary device drawing power from a generator at a power interface. Power supplied to the auxiliary device is regulated by the controller through signals transmitted over the communication link.
    Type: Grant
    Filed: April 4, 2019
    Date of Patent: September 7, 2021
    Assignee: Ford Global Technologies, LLC
    Inventors: Stuart Salter, Ross Dykstra Pursifull, Paul Kenneth Dellock, David Brian Glickman, William Taylor
  • Patent number: 11104430
    Abstract: A powertrain for a rotorcraft includes first and second engines and a transmission system that includes a main rotor gearbox, a first freewheeling unit coupling the first engine to the main rotor gearbox and a second freewheeling unit coupling the second engine to the main rotor gearbox. The first freewheeling unit has a driving configuration and a bypass configuration. In a preflight configuration of the rotorcraft, the first engine provides power to at least one auxiliary component with the first freewheeling unit in the bypass configuration while the second engine provides power to the main rotor. In a flight configuration of the rotorcraft, the first engine provides power to the main rotor with the first freewheeling unit in the driving configuration while the second engine also provides power to the main rotor.
    Type: Grant
    Filed: September 27, 2019
    Date of Patent: August 31, 2021
    Assignee: Textron Innovations Inc.
    Inventors: Carlos Alexander Fenny, Gilberto Morales, Ryan Thomas Ehinger
  • Patent number: 11084591
    Abstract: An aircraft cabin blower system includes a transmission configured to receive mechanical power from a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and power management system, wherein, when operating in a blower mode, the first electrical receives mechanical power from the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine acts as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system. The transmission's output drives a cabin blower compressor when operating in the blower mode, a speed of the output of the transmission being determined by a function of a speed of the first and second transmission inputs.
    Type: Grant
    Filed: January 3, 2019
    Date of Patent: August 10, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Glenn A Knight, Richard Sharpe
  • Patent number: 10988266
    Abstract: An auxiliary power unit (APU) control system for an aircraft is disclosed. The APU control system includes an APU, one or more processors, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the APU control system to receive a one or more ambient signals indicative of an air density value and one or more power signals indicative of a specific amount of power generated by the APU. The APU control system is further caused to determine a variable rotational speed of the APU based on the air density value and instruct the APU to operate at the variable rotational speed. The APU continues to generate the specific amount of power when operating at the variable rotational speed.
    Type: Grant
    Filed: January 29, 2019
    Date of Patent: April 27, 2021
    Assignee: The Boeing Company
    Inventor: Jeffrey J. White
  • Patent number: 10830149
    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor is connected to be driven with at least one rotor in the main compressor section. A source of pressurized air is selectively sent to the cooling compressor to drive a rotor of the cooling compressor to rotate, and to in turn drive the at least one rotor of the main compressor section at start-up of the gas turbine engine. An intercooling system is also disclosed.
    Type: Grant
    Filed: August 9, 2018
    Date of Patent: November 10, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nathan Snape, Gabriel L. Suciu, Brian D. Merry
  • Patent number: 10808611
    Abstract: A system for providing auxiliary power in an aircraft. A propulsion core comprises a compressor, a combustor, a turbine, and a shaft. An accessory unit comprises an accessory combustor, an accessory turbine, and an accessory shaft. A tank is configured to hold high pressure air and operably connected to the accessory unit. An electric generator comprises an electrical output and a mechanical input, with the mechanical input operably connected to the accessory shaft and the electrical output operably connected to an electric motor operably connected to the shaft. The electrical output is operably connected to an auxiliary power consuming device in the aircraft.
    Type: Grant
    Filed: August 26, 2019
    Date of Patent: October 20, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Michael Abraham Karam
  • Patent number: 10598095
    Abstract: Systems and methods for starting an engine on an aircraft are provided. One example aspect of the present disclosure is directed to an integrated starter for starting an engine on an aircraft. The integrated starter includes an air turbine starter. The integrated starter includes a starter air valve integrated with the air turbine starter. The integrated starter includes a controller configured to control the starter air valve. The starter air valve can be movable between a first position and at least a second position to regulate the flow of fluid into the air turbine starter. An output torque of the air turbine starter can be dependent at least in part on the flow of fluid into the air turbine starter.
    Type: Grant
    Filed: October 11, 2016
    Date of Patent: March 24, 2020
    Assignee: Unison Industries, LLC
    Inventors: Brian Christopher Kemp, Theodore Scott Puterbaugh
  • Patent number: 10519867
    Abstract: An integrated inlet particle separator (IPS) blower/engine starter including a housing having an inlet and an outlet. A turbine member is rotatably supported in the housing. A geared member operatively connected to the turbine member extends outward from the housing. The integrated IPS blower/engine starter is operable in a first configuration receiving a first fluid flow to rotate the geared member and in a second configuration generating a fluid flow through powered rotation of the geared member.
    Type: Grant
    Filed: September 27, 2017
    Date of Patent: December 31, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Joseph Lawrence Simonetti, Andrew G. Keith
  • Patent number: 10247193
    Abstract: A gas turbine engine includes a bearing support positioned fore of a compressor section along a primary flowpath. The bearing support internally includes a fluid reservoir with a reservoir tube, a fluid pump with a fluid pump tube, and a fluid coupler coupling the reservoir tube to the fluid pump tube.
    Type: Grant
    Filed: September 8, 2014
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventors: Todd M. LaPierre, Yuk-Kwan Brian Yuen
  • Patent number: 10107190
    Abstract: In a power generation system, exhausted fuel gas exhausted from a solid oxide fuel cell (SOFC) is used as a fuel of a first combustor or a second combustor of a gas turbine, and at the same time, a part of compressed air compressed by a compressor of the gas turbine is used to drive the SOFC. The gas turbine includes the first combustor for burning fuel gas which is different from the exhausted fuel gas, a first turbine configured to be driven by combustion gas supplied from the first combustor, the second combustor for burning at least a part of the exhausted fuel gas, and a second turbine coupled with the first turbine and configured to be driven by combustion gas supplied from the second combustor.
    Type: Grant
    Filed: November 5, 2013
    Date of Patent: October 23, 2018
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: So Manabe, Kentaro Fujii
  • Patent number: 9500137
    Abstract: A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply.
    Type: Grant
    Filed: January 28, 2016
    Date of Patent: November 22, 2016
    Assignee: TURBOMECA
    Inventor: Jean-Michel Haillot
  • Patent number: 9239011
    Abstract: A method of inhibiting ice accretion within a turbine engine, including the steps: (a) operating the turbine engine at a predetermined engine speed; and (b) driving the compressor of the turbine engine at an elevated speed which is greater than the nominal speed of the compressor at the predetermined engine speed so as to inhibit ice accretion within the compressor.
    Type: Grant
    Filed: July 11, 2012
    Date of Patent: January 19, 2016
    Assignee: ROLLS-ROYCE plc
    Inventor: Alan R. Jones
  • Patent number: 9217374
    Abstract: The present invention proposes a structural unit for an aircraft engine having at least one fuel pump of a fuel circuit and at least one hydraulic fluid pump of a hydraulic fluid circuit, where the structural unit can be coupled to an accessory gearbox shaft of an accessory gearbox of the engine.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: December 22, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Juergen Beier
  • Patent number: 9200592
    Abstract: A gas turbine engine includes a high spool, a low spool mechanically connected to a fan, a gear system, an actuator, and a starter. The gear system is actuable to engage and disengage the low spool to and from the high spool. The actuator is connected to the gear system for selectively engaging and disengaging the gear system. The starter is connected to the low spool and can drive rotation of the high spool through the low spool when the gear system is engaged.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: December 1, 2015
    Assignee: United Technologies Corporation
    Inventors: Andrew P. Berryann, Gabriel L. Suciu
  • Patent number: 9032703
    Abstract: In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting a flame holding condition about a fuel injector. The method may include the steps of: detecting an upstream pressure upstream of the secondary fuel injector; detecting a downstream pressure downstream of the secondary fuel injector; determining a measured pressure difference between the upstream pressure and the downstream pressure; and comparing the measured pressure difference to an expected pressure difference.
    Type: Grant
    Filed: June 20, 2011
    Date of Patent: May 19, 2015
    Assignee: General Electric Company
    Inventors: Anthony Wayne Krull, Gilbert Otto Kraemer, Garth Curtis Frederick, David Kaylor Toronto
  • Publication number: 20150107263
    Abstract: A control valve for a gas turbine engine air starter. The control valve includes a spherical or ball valve element rotatable between a closed position and an open position to connect an internal flow passage to the air starter. A series of camming elements interconnecting a piston and a valve stem for the spherical valve element convert linear displacement of the piston into rotational movement of the valve for rapid opening.
    Type: Application
    Filed: October 10, 2014
    Publication date: April 23, 2015
    Applicant: PHD, Inc.
    Inventor: Nelson Broman
  • Publication number: 20150082805
    Abstract: An air turbine starter includes a starter housing and a check valve. The check valve is disposed within the starter housing and is configured, in response to a pressure differential across the check valve, to selectively allow and prevent lubricant to flow therefrom. The check valve includes a valve includes a valve body, a valve seat, a valve bore, a valve element, and a plurality of rounded grooves. The valve bore is formed in the valve body between the valve seat and the lubricant outlet port. The valve element is disposed within the valve bore and is movable between a plurality of open positions and a closed position. The rounded grooves are formed in the valve body, and are disposed adjacent to, and in fluid communication with, the valve bore to improve lubricant to flow past the valve element when the valve element is in an open position.
    Type: Application
    Filed: September 23, 2013
    Publication date: March 26, 2015
    Inventors: Peter Kenneth Zeiner, Benjamin Ho, Cindy Byers
  • Patent number: 8973266
    Abstract: A gear cage assembly configured to support a plurality of planet gear in an air turbine starter is provided including a main plate and a back plate. The main plate includes a plurality of legs that extend from a first surface. A pin protrudes from a one of the plurality of legs. A plurality of shallow openings formed in the first surface extends over only a portion of a depth of the main plate. The back plate includes a plurality of bearing holes substantially identical to the plurality of shallow openings. A biasing mechanism and at least one alignment feature protrude from the back plate. The at least one alignment feature and the biasing mechanism are configured to contact at least one of the plurality of legs. A bushing mounted within the back plate is configured to receive the pin.
    Type: Grant
    Filed: November 9, 2012
    Date of Patent: March 10, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Yiwei Jiang, Jeffrey M. Makulec, Bradley Thomas Ryan