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).
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Patent number: 11673678Abstract: 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: GrantFiled: April 18, 2022Date of Patent: June 13, 2023Assignee: General Electric CompanyInventors: Jeffrey Anthony Hamel, Kurt David Murrow
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Publication number: 20220234746Abstract: 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: ApplicationFiled: April 18, 2022Publication date: July 28, 2022Inventors: Jeffrey Anthony Hamel, Kurt David Murrow
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Patent number: 11312502Abstract: 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: GrantFiled: August 16, 2019Date of Patent: April 26, 2022Assignee: General Electric CompanyInventors: Jeffrey Anthony Hamel, Kurt David Murrow
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Patent number: 11190267Abstract: A drone communication system is described. Using the system, a method may be executed that includes: when a recipient vehicle is out of wireless range, transmitting a message, from a sending vehicle, to a plurality of drones that are focusing antenna beams on the sending vehicle so that the plurality then may transmit the message to the recipient vehicle by focusing antenna beams thereon.Type: GrantFiled: August 24, 2017Date of Patent: November 30, 2021Assignee: FORD GLOBAL TECHNOLOGIES, LLCInventors: Perry Robinson MacNeille, Jeffrey Anthony Hamel, John Jeffrey Pfeiffer, Doug Moore
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Publication number: 20210126703Abstract: A drone communication system is described. Using the system, a method may be executed that includes: when a recipient vehicle is out of wireless range, transmitting a message, from a sending vehicle, to a plurality of drones that are focusing antenna beams on the sending vehicle so that the plurality then may transmit the message to the recipient vehicle by focusing antenna beams thereon.Type: ApplicationFiled: August 24, 2017Publication date: April 29, 2021Inventors: Perry Robinson MACNEILLE, Jeffrey Anthony HAMEL, John Jeffrey PFEIFFER, Doug MOORE
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Patent number: 10720804Abstract: 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 including a stator winding to produce electrical currents. The stator assembly extending along a longitudinal axis with an inner surface defining a cavity. The rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and rotates about the longitudinal axis. The rotor assembly including a plurality of permanent magnets for generating a magnetic field which interacts with the stator winding to produce the electrical currents in response to rotation of the rotor assembly. within one or more cavities formed in a sleeve component. The sleeve component is configured to include a plurality of cavities or voids into which the permanent magnets are disposed to retain the permanent magnets therein and form an interior permanent magnet generator.Type: GrantFiled: June 27, 2019Date of Patent: July 21, 2020Assignee: General Electric CompanyInventors: Narendra Digamber Joshi, Manoj Ramprasad Shah, James William Bray, Randy Marinus Vondrell, Kurt David Murrow, Jeffrey Anthony Hamel, Samuel Jacob Martin
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Publication number: 20200122849Abstract: 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: ApplicationFiled: August 16, 2019Publication date: April 23, 2020Inventors: Jeffrey Anthony Hamel, Kurt David Murrow
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Patent number: 10487739Abstract: 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: GrantFiled: July 20, 2015Date of Patent: November 26, 2019Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Jeffrey Anthony Hamel
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Publication number: 20190326789Abstract: 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 including a stator winding to produce electrical currents. The stator assembly extending along a longitudinal axis with an inner surface defining a cavity. The rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and rotates about the longitudinal axis. The rotor assembly including a plurality of permanent magnets for generating a magnetic field which interacts with the stator winding to produce the electrical currents in response to rotation of the rotor assembly. within one or more cavities formed in a sleeve component. The sleeve component is configured to include a plurality of cavities or voids into which the permanent magnets are disposed to retain the permanent magnets therein and form an interior permanent magnet generator.Type: ApplicationFiled: June 27, 2019Publication date: October 24, 2019Inventors: Narendra Digamber Joshi, Manoj Ramprasad Shah, James William Bray, Randy Marinus Vondrell, Kurt David Murrow, Jeffrey Anthony Hamel, Samuel Jacob Martin
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Patent number: 10414508Abstract: 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: GrantFiled: May 11, 2018Date of Patent: September 17, 2019Assignee: General Electric CompanyInventors: Jeffrey Anthony Hamel, Kurt David Murrow
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Patent number: 10381889Abstract: 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: GrantFiled: June 27, 2014Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: Narendra Digamber Joshi, Manoj Ramprasad Shah, James William Bray, Randy Marinus Vondrell, Kurt David Murrow, Jeffrey Anthony Hamel, Samuel Jacob Martin
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Publication number: 20180257787Abstract: 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: ApplicationFiled: May 11, 2018Publication date: September 13, 2018Inventors: Jeffrey Anthony Hamel, Kurt David Murrow
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Patent number: 10000293Abstract: 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: GrantFiled: December 15, 2015Date of Patent: June 19, 2018Assignee: General Electric CompanyInventors: Jeffrey Anthony Hamel, Kurt David Murrow
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Patent number: 9995314Abstract: 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: GrantFiled: July 20, 2015Date of Patent: June 12, 2018Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Jeffrey Anthony Hamel
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Patent number: 9777642Abstract: 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: GrantFiled: October 22, 2015Date of Patent: October 3, 2017Assignee: General Electric CompanyInventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Randy M. Vondrell, Tsuguji Nakano, Jeffrey Anthony Hamel, Darek Tomasz Zatorski
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Patent number: 9771878Abstract: A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided.Type: GrantFiled: October 19, 2015Date of Patent: September 26, 2017Assignee: General Electric CompanyInventors: Manxue Lu, Jeffrey Anthony Hamel
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Publication number: 20170107914Abstract: A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided.Type: ApplicationFiled: October 19, 2015Publication date: April 20, 2017Inventors: Manxue Lu, Jeffrey Anthony Hamel
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Publication number: 20170023018Abstract: 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: ApplicationFiled: July 20, 2015Publication date: January 26, 2017Inventors: Brandon Wayne MILLER, Jeffrey Anthony HAMEL
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Publication number: 20170022900Abstract: 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: ApplicationFiled: July 20, 2015Publication date: January 26, 2017Inventors: Brandon Wayne MILLER, Jeffrey Anthony HAMEL
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Publication number: 20160214727Abstract: 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: ApplicationFiled: December 15, 2015Publication date: July 28, 2016Inventors: Jeffrey Anthony HAMEL, Kurt David MURROW