Patents by Inventor Joseph Turney

Joseph Turney has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 11884409
    Abstract: Aircraft electric motors include a motor unit having a rotor and a stator. The stator includes a plurality of windings and cooling channels arranged to provide cooling thereto. A drive unit is configured to drive operation of the motor unit. A cooling system includes a working fluid arranged within a cooling fluid flow path, wherein the cooling fluid flow path includes a liquid cooling path configured to direct flow of the working fluid through, at least, the cooling channels of the motor unit and a vapor cooling path configured to direct flow of the working fluid through the drive unit and a separator arranged upstream of each of the liquid cooling path and the vapor cooling path and configured to direct a liquid portion of the working fluid into the liquid cooling path and configured to direct a vapor portion of the working fluid into the vapor cooling path.
    Type: Grant
    Filed: November 1, 2021
    Date of Patent: January 30, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Abbas A Alahyari, Kimberly Rae Saviers, Joseph Turney, Jagadeesh Kumar Tangudu
  • Patent number: 11817761
    Abstract: Aircraft electric motors are described. The aircraft electric motors include a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings, a drive unit configured to drive operation of the motor unit, and a cooling system having at least one directional feature forming a portion of at least one cooling channel, the at least one directional feature configured to prevent backflow of a cooling fluid that passes through the at least one cooling channel.
    Type: Grant
    Filed: November 5, 2021
    Date of Patent: November 14, 2023
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Abbas A. Alahyari, Joseph Turney, Jagadeesh Kumar Tangudu, Kimberly Rae Saviers
  • Patent number: 11773780
    Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a turbine section, with both the main compressor section and the turbine section housing rotatable components. A first tap taps air compressed by the main compressor section at an upstream location upstream of the downstream most location. The first tap passes through a heat exchanger, and to a cooling compressor. Air downstream of the cooling compressor is selectively connected to reach at least one of the rotatable components. The cooling compressor is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section and the turbine section. A valve system includes a check valve for selectively blocking flow downstream of the cooling compressor from reaching the at least one rotatable component. A dump valve selectively dumps air downstream of the cooling compressor. A method is also disclosed.
    Type: Grant
    Filed: January 28, 2022
    Date of Patent: October 3, 2023
    Assignee: RTX CORPORATION
    Inventor: Joseph Turney
  • Publication number: 20230288143
    Abstract: A heat exchanger includes a heat exchanger body having a first end and a second end opposed to the first end along a flow axis. A plurality of flow channels is defined in the heat exchanger body extending axially with respect to the flow axis. A first set of the flow channels forms a first flow circuit and a second set of the flow channels forms a second flow circuit that is in fluid isolation from the first flow circuit. Each flow channel is fluidly isolated from the other flow channels. The flow channels all conform to a curvilinear profile.
    Type: Application
    Filed: May 16, 2023
    Publication date: September 14, 2023
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Joseph Turney, Ram Ranjan, Thomas M. Yun, Matthew Robert Pearson
  • Patent number: 11705782
    Abstract: A stator and a motor including a stator. The stator includes a stator hub, a plurality of stator teeth extending from the stator hub that define a stator slot having a stator slot base, at least one winding disposed in the stator slot, and one or more oscillating heat pipes disposed at least partially in the at least one winding. The at least one winding is held apart from the stator slot base so that a cooling channel is defined between an inner winding portion of the at least one winding and a portion of the one or more oscillating heat pipes is disposed in the channel so cooling fluid can be passed between the stator slot base and the inner winding portion to cool the inner winding portion via at least operation of the one or more oscillating heat pipes.
    Type: Grant
    Filed: September 23, 2021
    Date of Patent: July 18, 2023
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Abbas A. Alahyari, Kimberly Rae Saviers, Jagadeesh Kumar Tangudu, Joseph Turney
  • Publication number: 20230220999
    Abstract: A combustor for a detonation engine includes a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned at least partially within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a cooling flow passage defined along at least one of the radially outer wall and the radially inner wall and comprising at least two axially spaced cooling flow passage sections, whereby a different cooling rate can be implemented in the at least two axially spaced cooling flow passage sections.
    Type: Application
    Filed: April 9, 2021
    Publication date: July 13, 2023
    Applicant: Raytheon Technologies Corporation
    Inventors: Joseph Turney, Christopher Britton Greene, Peter AT Cocks, Andrzej Ernest Kuczek, James M. Donohue
  • Patent number: 11692780
    Abstract: A counter-flow heat exchanger comprising a heat exchanger core including an inner wall and an outer wall radially outward and spaced apart from the inner wall. A first flow path is defined within the inner wall and a second flow path is defined between the inner wall and the outer wall. The heat exchanger core includes a primary flow inlet, a primary flow outlet and a middle portion therebetween. The inner and outer walls are concentric at the primary flow inlet of the heat exchanger core. The inner wall defines a first set of channels extending axially from the primary flow inlet to the middle portion of the heat exchanger core diverging away from a radial center of the heat exchanger core. The inner wall and the outer wall define a second set of channels extending axially from the primary flow inlet to the middle portion of the heat exchanger core converging toward the radial center of the heat exchanger core.
    Type: Grant
    Filed: February 15, 2021
    Date of Patent: July 4, 2023
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Joseph Turney
  • Publication number: 20230143600
    Abstract: Aircraft electric motors are described. The aircraft electric motors include a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings, a drive unit configured to drive operation of the motor unit, and a cooling system. The cooling system includes an oscillating heat pipe containing a first working fluid, wherein the oscillating heat pipe is arranged to pick up heat from at least one winding, the oscillating heat pipe having an evaporator section arranged in thermal contact with the at least one winding and a condenser section arranged away from the evaporator section and a heat pickup portion arranged to receive a second working fluid to remove heat from the condenser section of the oscillating heat pipe.
    Type: Application
    Filed: November 5, 2021
    Publication date: May 11, 2023
    Inventors: Kimberly Rae Saviers, Abbas A. Alahyari, Jagadeesh Kumar Tangudu, Joseph Turney
  • Publication number: 20230142019
    Abstract: Aircraft electric motors are described. The aircraft electric motors includes a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings, a drive unit configured to drive operation of the motor unit, and a cooling system. The cooling system includes at least one cooling channel integrally formed within at least one winding, wherein the at least one cooling channel comprises an inlet to receive a two-phase cooling fluid and an outlet configured to discharge the two-phase cooling fluid, wherein a cross-sectional area of the at least one cooling channel at the inlet is less than a cross-sectional area of the at least one cooling channel at the outlet.
    Type: Application
    Filed: November 9, 2021
    Publication date: May 11, 2023
    Inventors: Kimberly Rae Saviers, Abbas A. Alahyari, Jagadeesh Kumar Tangudu, Joseph Turney
  • Publication number: 20230141526
    Abstract: Aircraft electric motors are described. The aircraft electric motors include a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings, a drive unit configured to drive operation of the motor unit, and a cooling system having at least one directional feature forming a portion of at least one cooling channel, the at least one directional feature configured to prevent backflow of a cooling fluid that passes through the at least one cooling channel.
    Type: Application
    Filed: November 5, 2021
    Publication date: May 11, 2023
    Inventors: Abbas A. Alahyari, Joseph Turney, Jagadeesh Kumar Tangudu, Kimberly Rae Saviers
  • Publication number: 20230138133
    Abstract: Aircraft electric motors include a motor unit having a rotor and a stator. The stator includes a plurality of windings and cooling channels arranged to provide cooling thereto. A drive unit is configured to drive operation of the motor unit. A cooling system includes a working fluid arranged within a cooling fluid flow path, wherein the cooling fluid flow path includes a liquid cooling path configured to direct flow of the working fluid through, at least, the cooling channels of the motor unit and a vapor cooling path configured to direct flow of the working fluid through the drive unit and a separator arranged upstream of each of the liquid cooling path and the vapor cooling path and configured to direct a liquid portion of the working fluid into the liquid cooling path and configured to direct a vapor portion of the working fluid into the vapor cooling path.
    Type: Application
    Filed: November 1, 2021
    Publication date: May 4, 2023
    Inventors: Abbas A. Alahyari, Kimberly Rae Saviers, Joseph Turney, Jagadeesh Kumar Tangudu
  • Publication number: 20230123004
    Abstract: A cold plate apparatus is disclosed. A cold plate includes a first set of sinusoidal conduits and a second set of sinusoidal conduits formed therein. The first set of sinusoidal conduits is arranged in a first direction, and the second set of sinusoidal conduits is arranged in a second direction. Crests of the first set of sinusoidal conduits overlap troughs of the second set of sinusoidal conduits. Crests of the second set of sinusoidal conduits overlap troughs of the first set of sinusoidal conduits. A first set of header plates is fluidically coupled to the first set of sinusoidal conduits, and a second set of header plates is fluidically coupled to the second set of sinusoidal conduits.
    Type: Application
    Filed: October 19, 2021
    Publication date: April 20, 2023
    Inventors: Joseph Turney, Kimberly Saviers, Ram Ranjan, Robert H. Dold, Kathryn L. Kirsch
  • Publication number: 20230116443
    Abstract: A header for a high-pressure heat exchanger includes a first high-pressure transition section with inlets for multiple first high-pressure flow channels that are spaced from one another in a radial direction and collectively arranged in a substantially circular shape. The inlets for the multiple first high-pressure flow channels on a radially outer edge of the first high-pressure transition section are spaced further apart in a circumferential direction from adjacent inlets of the multiple first high-pressure flow channels than radially inward inlets are spaced from adjacent radially inward inlets of the multiple first high-pressure flow channels. The header also includes multiple first high-pressure flow channels extending from the first high-pressure transition section to a second-high pressure transition section that is configured to divide each of the multiple first high-pressure flow channels into at least two first high-pressure sub-flow channels.
    Type: Application
    Filed: October 4, 2022
    Publication date: April 13, 2023
    Inventors: Kathryn L. Kirsch, Robert H. Dold, Paul Attridge, Alexandru Cadar, Joseph Turney, Ram Ranjan
  • Publication number: 20230090559
    Abstract: A stator and a motor including a stator. The stator includes a stator hub, a plurality of stator teeth extending from the stator hub that define a stator slot having a stator slot base, at least one winding disposed in the stator slot, and one or more oscillating heat pipes disposed at least partially in the at least one winding. The at least one winding is held apart from the stator slot base so that a cooling channel is defined between an inner winding portion of the at least one winding and a portion of the one or more oscillating heat pipes is disposed in the channel so cooling fluid can be passed between the stator slot base and the inner winding portion to cool the inner winding portion via at least operation of the one or more oscillating heat pipes.
    Type: Application
    Filed: September 23, 2021
    Publication date: March 23, 2023
    Inventors: Abbas A. Alahyari, Kimberly Rae Saviers, Jagadeesh Kumar Tangudu, Joseph Turney
  • Publication number: 20230083470
    Abstract: Aircraft systems including a fuel tank containing a cryogenic fuel, an engine configured to consume the fuel, and an ECS having a precooler arranged to receive the fuel and air from the engine. The precooler includes a first heat exchanger configured to receive a first state of the fuel and output a second state of the fuel and a second heat exchanger configured to receive the second state fuel and output a third state fuel. The first state has a first density, the second state has a second density, and the third state has a third density, wherein the first density is greater than the second density, and the second density is greater than the third density. The engine air is directed through the second heat exchanger first and then through the first heat exchanger.
    Type: Application
    Filed: September 10, 2021
    Publication date: March 16, 2023
    Inventors: Ram Ranjan, Matthew Robert Pearson, Joseph Turney
  • Publication number: 20230080053
    Abstract: An environmental control system (ECS) for an aircraft includes a primary heat exchanger, a compressor including an inlet fluidically connected to the primary heat exchanger, a turbine operatively connected to the compressor, and a cryogenic fluid heat exchanger fluidically connected to the primary heat exchanger.
    Type: Application
    Filed: September 10, 2021
    Publication date: March 16, 2023
    Inventors: Sean C. Emerson, Giusi Quartarone, Joseph Turney, Ram Ranjan, Erica Zavaglio, Federico Mattia Benzi, Charles E. Lents
  • Publication number: 20230077242
    Abstract: Aircraft fuel system including a fuel vessel containing a non-mixture fuel. A protective vessel is arranged about the fuel vessel such that the fuel vessel is contained within the protective vessel and a protective space is defined between an outer surface of a vessel wall of the fuel vessel and an inner surface of a vessel wall of the protective vessel. At least one mounting structure fixedly positions the fuel vessel within the protective vessel. A fuel consumption device configured to consume the non-mixture fuel. A fuel output fluidly connects an interior of the fuel vessel to the fuel consumption device, the fuel output being fluidly isolated from the protective space. A relief output fluidly connects the protective space to a relief flow path, the relief output and relief flow path configured to vent gas from the protective space and remove any non-mixture fuel from the protective space.
    Type: Application
    Filed: September 9, 2021
    Publication date: March 9, 2023
    Inventors: Sean C. Emerson, Paul Papas, Joseph Turney, Ram Ranjan
  • Patent number: 11518537
    Abstract: Fuel tank inerting systems are provided. The systems include a fuel tank, an air source arranged to supply air into a reactive flow path, a catalytic reactor having a plurality of sub-reactors along the flow path, and a heat exchanger. The sub-reactors are arranged relative to the heat exchanger such that the flow path passes through at least a portion of the heat exchanger between two sub-reactors along the flow path. At least one fuel injector is arranged relative to at least one sub-reactor. The fuel injector is configured to inject fuel into the flow path at at least one of upstream of and in the respective at least one sub-reactor to generate a fuel-air mixture. A fuel tank ullage supply line fluidly connects the flow path to the fuel tank to supply an inert gas to a ullage of the fuel tank.
    Type: Grant
    Filed: June 21, 2018
    Date of Patent: December 6, 2022
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Sean C. Emerson, Zissis A. Dardas, Robert R. Hebert, Randolph Carlton McGee, Allen Murray, Eric Surawski, Joseph Turney
  • Patent number: 11493286
    Abstract: A header for a high-pressure heat exchanger includes a first high-pressure transition section with inlets for multiple first high-pressure flow channels that are spaced from one another in a radial direction and collectively arranged in a substantially circular shape. The inlets for the multiple first high-pressure flow channels on a radially outer edge of the first high-pressure transition section are spaced further apart in a circumferential direction from adjacent inlets of the multiple first high-pressure flow channels than radially inward inlets are spaced from adjacent radially inward inlets of the multiple first high-pressure flow channels. The header also includes multiple first high-pressure flow channels extending from the first high-pressure transition section to a second-high pressure transition section that is configured to divide each of the multiple first high-pressure flow channels into at least two first high-pressure sub-flow channels.
    Type: Grant
    Filed: October 12, 2021
    Date of Patent: November 8, 2022
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Kathryn L. Kirsch, Robert H. Dold, Paul Attridge, Alexandru Cadar, Joseph Turney, Ram Ranjan
  • Patent number: 11448466
    Abstract: A heat exchanger including a plurality of tubes, a header, and a plurality of flow voids. The plurality of tubes extends in a first direction through which a first fluid is configured to flow. Each of the plurality of tubes have waves that repeat at regular intervals along the first flow direction and are spaced from one another vertically and laterally in the second direction. The header extends in the first direction and is attached to each of the plurality of tubes. The header is configured to convey the first fluid to each of the plurality of tubes. The plurality of flow voids are formed between the plurality of tubes. The plurality of flow voids extend in a second direction through which a second fluid is configured to flow such that the second fluid is in thermal contact with the plurality of tubes.
    Type: Grant
    Filed: December 9, 2020
    Date of Patent: September 20, 2022
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Joseph Turney, Robert H. Dold, Christopher Britton Greene, John H. Whiton