Patents by Inventor Ram Ranjan

Ram Ranjan 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: 11912416
    Abstract: Aircraft systems including a pressurized fuel tank containing a pressurized fuel, a turbo expander configured to receive the pressurized fuel from the fuel tank, the turbo expander configured to decrease a pressure of the pressurized fuel to generate low pressure fuel having pressure less than the pressurized fuel, a fuel-to-air heat exchanger configured to receive the low pressure fuel from the turbo expander as a first working fluid and air as a second working fluid, the heat exchanger configured to cool the air and warm the fuel, an aircraft cabin configured to receive the cooled air, and a fuel consumption system configured to consume the fuel to generate power.
    Type: Grant
    Filed: September 9, 2021
    Date of Patent: February 27, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Giusi Quartarone, Erica Zavaglio, Federico Mattia Benzi, Ram Ranjan
  • Patent number: 11876405
    Abstract: A stator of an electric motor includes a stator core including a rim and a plurality of stator teeth extending from the rim. The plurality of stator teeth define a plurality of tooth gaps between circumferentially adjacent stator teeth. A plurality of stator windings are wrapped along the plurality of stator teeth. The plurality of stator windings include a plurality of core segments extending along the plurality of tooth gaps, and a plurality of end turn segments connecting adjacent core segments. A plurality of non-electrically conductive cooling channels are located in the stator core. The plurality of cooling channels are configured to direct a cooling fluid flow therethrough to cool the plurality of stator windings.
    Type: Grant
    Filed: January 14, 2020
    Date of Patent: January 16, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Kimberly Rae Saviers, Ram Ranjan, Jagadeesh Kumar Tangudu
  • Publication number: 20230384044
    Abstract: A method of manufacturing a heat exchanger core from glass ceramic matrix composite includes placing one or more reinforcing fibers around one or more mandrels into a mold cavity. A glass matrix material infiltrates the one or more reinforcing fibers to produce an infiltrated core and the one or more mandrels is removed to create one or more passages passing through the infiltrated core.
    Type: Application
    Filed: May 26, 2022
    Publication date: November 30, 2023
    Inventors: John Joseph Gangloff, Paul Sheedy, Justin B. Alms, Kathryn L. Kirsch, Thomas M. Yun, Daniel A. Mosher, John E. Holowczak, Ram Ranjan
  • Publication number: 20230349296
    Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.
    Type: Application
    Filed: May 22, 2023
    Publication date: November 2, 2023
    Inventors: Zhongtao Dai, Ram Ranjan, Robert H. Dold
  • Publication number: 20230314091
    Abstract: A heat sink with a primary flow volume, an inlet, an outlet, a bottom plate, a top plate, distribution, heat transfer and collector sections, and flow paths between pillars. The inlet cross-section defines the primary flow volume cross-section and the length of the primary flow volume extends into the heat sink at a right angle to the inlet cross-section. The distribution section is proximate to the flow inlet and has distribution pillars extending from the bottom or top plate. The heat transfer section is proximate to the distribution section and has heat transfer pillars extending from the bottom or top plate. The collector section is proximate to the heat transfer section and has collector pillars extending from the bottom or top plate. The distribution cross-section is greater than the heat transfer cross-section which is smaller than the collector cross-section. The flow paths extend outside of the primary flow volume.
    Type: Application
    Filed: April 1, 2022
    Publication date: October 5, 2023
    Inventors: Ram Ranjan, Kimberly R. Saviers, Kathryn L. Kirsch, Ross K. Wilcoxon
  • Publication number: 20230313711
    Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.
    Type: Application
    Filed: February 14, 2023
    Publication date: October 5, 2023
    Inventors: Malcolm P. MacDonald, Stephen H. Taylor, Ram Ranjan
  • Publication number: 20230314092
    Abstract: A heat sink with a primary flow volume, an inlet, an outlet, a bottom plate, a top plate, distribution, heat transfer and collector sections, and flow paths between pillars. The inlet cross-section defines the primary flow volume cross-section and the length of the primary flow volume extends into the heat sink at a right angle to the inlet cross-section. The distribution section is proximate to the flow inlet and has distribution pillars extending from the bottom or top plate. The heat transfer section is proximate to the distribution section and has heat transfer pillars extending from the bottom or top plate. The collector section is proximate to the heat transfer section and has collector pillars extending from the bottom or top plate. The distribution cross-section is greater than the heat transfer cross-section which is smaller than the collector cross-section. The outlet and the flow paths extend outside of the primary flow volume.
    Type: Application
    Filed: April 1, 2022
    Publication date: October 5, 2023
    Inventors: Ram Ranjan, Kimberly R. Saviers, Kathryn L. Kirsch, Ross K. Wilcoxon
  • 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: 11731780
    Abstract: An aircraft system includes a turbine engine having a compressor, a combustor having an inlet and an outlet, and a turbine having an inlet portion and an outlet portion. An auxiliary power unit (APU) is operatively connected to the turbine engine. The APU includes a compressor portion, a generator, and a turbine portion. The compressor portion is operatively connected to the turbine portion through the generator. A source of cryogenic fluid is operatively connected to the turbine engine and the APU. A heat exchange member includes an inlet section operatively connected to the source of cryogenic fluid, a first outlet section operatively connected to the turbine engine and a second outlet section operatively connected to the compressor portion.
    Type: Grant
    Filed: September 9, 2021
    Date of Patent: August 22, 2023
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Ram Ranjan
  • Patent number: 11680487
    Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.
    Type: Grant
    Filed: November 5, 2021
    Date of Patent: June 20, 2023
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Zhongtao Dai, Ram Ranjan, Robert H. Dold
  • Publication number: 20230146859
    Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.
    Type: Application
    Filed: November 5, 2021
    Publication date: May 11, 2023
    Inventors: Zhongtao Dai, Ram Ranjan, Robert H. Dold
  • 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
  • Patent number: 11629637
    Abstract: Power generation systems are described. The systems include a shaft, a compressor operably coupled to a first end of the shaft, a turbine operably coupled to a second end of the shaft, a generator operably coupled to the shaft between the compressor and the turbine, and a working fluid arranged in a closed-loop flow path that flows through each of the compressor and the turbine to drive rotation of the shaft. The shaft includes an internal fluid conduit configured to receive a portion of the working fluid at one of the first end and the second end and convey the portion of the working fluid through the generator to the other of the first end and the second end, wherein the portion of the working fluid is rejoined with a primary flow path of the working fluid.
    Type: Grant
    Filed: November 18, 2020
    Date of Patent: April 18, 2023
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Brian M. Holley, Ram Ranjan
  • 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: 20230077598
    Abstract: A system for cooling a power component includes a first metal layer. A cooling layer having a first surface is in contact with a surface of the first metal layer. A second metal layer is included having a surface in contact with a second surface of the cooling layer opposite the first metal layer. The cooling layer is of a material different from that of the first metal layer and that of the second metal layer. A plurality of cooling features are embedded in the material of the cooling layer. The cooling channels are spaced apart from both the first metal layer and the second metal layer by the material of the cooling layer. An electrically conductive path connects the first metal plate to the second metal plate.
    Type: Application
    Filed: September 14, 2021
    Publication date: March 16, 2023
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Jeffrey Ewanchuk, Kimberly Rae Saviers, Ram Ranjan, Ross Wilcoxon, Haley Steffen
  • 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: 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: 20230077343
    Abstract: An exhaust moisture removal system for an electric generation system including: a sorbent wheel; an interchanger; a hydrogen evaporator including an exhaust portion; and an exhaust outflow stream passageway configured to convey an exhaust from a hydrogen fuel cell of the electric generation system through a first pass and then through a second pass, the second pass being located downstream of the first pass, wherein the first pass of the exhaust outflow stream passageway passes through the sorbent wheel, then through the interchanger, and then through the hydrogen evaporator, and wherein the second pass of the exhaust outflow stream passageway passes through the hydrogen evaporator, then through the interchanger, and then through the sorbent wheel.
    Type: Application
    Filed: September 10, 2021
    Publication date: March 16, 2023
    Inventors: Matthew Robert Pearson, Sean C. Emerson, Ram Ranjan
  • 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
  • Publication number: 20230075009
    Abstract: An aircraft system includes a turbine engine having a compressor, a combustor having an inlet and an outlet, and a turbine having an inlet portion and an outlet portion. An auxiliary power unit (APU) is operatively connected to the turbine engine. The APU includes a compressor portion, a generator, and a turbine portion. The compressor portion is operatively connected to the turbine portion through the generator. A source of cryogenic fluid is operatively connected to the turbine engine and the APU. A heat exchange member includes an inlet section operatively connected to the source of cryogenic fluid, a first outlet section operatively connected to the turbine engine and a second outlet section operatively connected to the compressor portion.
    Type: Application
    Filed: September 9, 2021
    Publication date: March 9, 2023
    Inventor: Ram Ranjan