Patents by Inventor Jeffrey Anthony Hamel

Jeffrey Anthony Hamel 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: 10414508
    Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
    Type: Grant
    Filed: May 11, 2018
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Jeffrey Anthony Hamel, Kurt David Murrow
  • Patent number: 10381889
    Abstract: A permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.
    Type: Grant
    Filed: June 27, 2014
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Narendra Digamber Joshi, Manoj Ramprasad Shah, James William Bray, Randy Marinus Vondrell, Kurt David Murrow, Jeffrey Anthony Hamel, Samuel Jacob Martin
  • Publication number: 20180257787
    Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
    Type: Application
    Filed: May 11, 2018
    Publication date: September 13, 2018
    Inventors: Jeffrey Anthony Hamel, Kurt David Murrow
  • Patent number: 10000293
    Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: June 19, 2018
    Assignee: General Electric Company
    Inventors: Jeffrey Anthony Hamel, Kurt David Murrow
  • Patent number: 9995314
    Abstract: A gas turbine engine including a compressor section and a turbine section, coupled by one or more shafts, is provided. The compressor section progressively compresses air and includes an aft-stage of rotor blades rotatable about an axial direction of the gas turbine engine. A cooling system is included with the gas turbine engine for cooling compressed air in or from the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and one or more fluid lines in fluid communication with the fluid tank. The one or more fluid lines include an outlet positioned adjacent to the aft-stage of rotor blades for injecting cooling fluid into the compressed air proximate the aft-stage of rotor blades.
    Type: Grant
    Filed: July 20, 2015
    Date of Patent: June 12, 2018
    Assignee: General Electric Company
    Inventors: Brandon Wayne Miller, Jeffrey Anthony Hamel
  • Patent number: 9777642
    Abstract: A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.
    Type: Grant
    Filed: October 22, 2015
    Date of Patent: October 3, 2017
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Randy M. Vondrell, Tsuguji Nakano, Jeffrey Anthony Hamel, Darek Tomasz Zatorski
  • Patent number: 9771878
    Abstract: A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided.
    Type: Grant
    Filed: October 19, 2015
    Date of Patent: September 26, 2017
    Assignee: General Electric Company
    Inventors: Manxue Lu, Jeffrey Anthony Hamel
  • Publication number: 20170107914
    Abstract: A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided.
    Type: Application
    Filed: October 19, 2015
    Publication date: April 20, 2017
    Inventors: Manxue Lu, Jeffrey Anthony Hamel
  • Publication number: 20170022900
    Abstract: A gas turbine engine including a compressor section, a turbine section, and a combustion section positioned between the compressor section and the turbine section is provided. The gas turbine engine also includes a cooling system having a tank and one or more fluid lines in fluid communication with the tank. The one or more fluid lines are configured to carry a flow of consumable cooling liquid provide such consumable cooling liquid to one or more components of the compressor section, the turbine section, and/or the combustion section not directly exposed to a core air flowpath defined through the gas turbine engine.
    Type: Application
    Filed: July 20, 2015
    Publication date: January 26, 2017
    Inventors: Brandon Wayne MILLER, Jeffrey Anthony HAMEL
  • Publication number: 20170023018
    Abstract: A gas turbine engine including a compressor section and a turbine section, coupled by one or more shafts, is provided. The compressor section progressively compresses air and includes an aft-stage of rotor blades rotatable about an axial direction of the gas turbine engine. A cooling system is included with the gas turbine engine for cooling compressed air in or from the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and one or more fluid lines in fluid communication with the fluid tank. The one or more fluid lines include an outlet positioned adjacent to the aft-stage of rotor blades for injecting cooling fluid into the compressed air proximate the aft-stage of rotor blades.
    Type: Application
    Filed: July 20, 2015
    Publication date: January 26, 2017
    Inventors: Brandon Wayne MILLER, Jeffrey Anthony HAMEL
  • Publication number: 20160214727
    Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
    Type: Application
    Filed: December 15, 2015
    Publication date: July 28, 2016
    Inventors: Jeffrey Anthony HAMEL, Kurt David MURROW
  • Publication number: 20160146115
    Abstract: A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.
    Type: Application
    Filed: October 22, 2015
    Publication date: May 26, 2016
    Inventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Randy M. Vondrell, Tsuguji Nakano, Jeffrey Anthony Hamel, Darek Tomasz Zatorski
  • Publication number: 20150380999
    Abstract: A permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.
    Type: Application
    Filed: June 27, 2014
    Publication date: December 31, 2015
    Inventors: Narendra Digamber Joshi, Manoj Ramprasad Shah, James William Bray, Randy Marinus Vondrell, Kurt David Murrow, Jeffrey Anthony Hamel, Samuel Jacob Martin