Patents by Inventor Thomas Edward Brinson
Thomas Edward Brinson 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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Publication number: 20220018262Abstract: The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first heat exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.Type: ApplicationFiled: September 30, 2021Publication date: January 20, 2022Inventors: Thomas Edward Brinson, Paul Robert Gemin
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Patent number: 11203949Abstract: The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.Type: GrantFiled: August 11, 2016Date of Patent: December 21, 2021Assignee: General Electric CompanyInventors: Thomas Edward Brinson, Paul Robert Gemin
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Patent number: 10815890Abstract: Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a VGT cooling system turbine (240) downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) for bypassing the turbine can also be included.Type: GrantFiled: June 30, 2015Date of Patent: October 27, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Kevin Richard Leamy, Benjamin Paul Breig, Michael Jay Epstein, Javier Armando Parrilla, Matthew John Hurt, Thomas Edward Brinson, Andrew James Fleming, George Eugene Wilmot
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Patent number: 10808618Abstract: Methods and devices for cooling systems (100, 700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a cooling system turbine (240) with variable guide vanes—VGT—and downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) can also be included that bypasses the cooling system turbine (240).Type: GrantFiled: June 30, 2015Date of Patent: October 20, 2020Assignee: General Electric CompanyInventors: Kevin Richard Leamy, Benjamin Paul Breig, Michael Jay Epstein, Javier Armando Parrilla, Matthew John Hurt, Thomas Edward Brinson, Andrew James Fleming, George Eugene Wilmot, Jr.
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Patent number: 10247100Abstract: Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.Type: GrantFiled: June 30, 2015Date of Patent: April 2, 2019Assignee: General Electric CompanyInventors: Kevin Richard Leamy, Benjamin Paul Breig, Michael Jay Epstein, Javier Armando Parrilla, Matthew John Hurt, Thomas Edward Brinson, Andrew James Fleming
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Publication number: 20180215475Abstract: Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.Type: ApplicationFiled: February 1, 2017Publication date: August 2, 2018Inventors: Matthew John Hurt, Robert Gregory Carita, Thomas Edward Brinson, Matthew Robert Cerny, Amit Kumar Misra-Martinez, David Vickery Parker, Alejandro Yatzail Perez Valdez
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Publication number: 20180194479Abstract: Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a VGT cooling system turbine (240) downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) for bypassing the turbine can also be included.Type: ApplicationFiled: June 30, 2015Publication date: July 12, 2018Inventors: Kevin Richard Leamy, Benjamin Paul Breig, Michael Jay Epstein, Javier Armando Parrilla, Matthew John Hurt, Thomas Edward Brinson, Andrew James Fleming, George Eugene Wilmot
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Publication number: 20180194480Abstract: Methods and devices for cooling systems (100, 700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a cooling system turbine (240) with variable guide vanes—VGT—and downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) can also be included that bypasses the cooling system turbine (240).Type: ApplicationFiled: June 30, 2015Publication date: July 12, 2018Inventors: Kevin Richard LEAMY, Benajamin Paul BREIG, Michael Jay EPSTEIN, Javier Armando PARRILLA, Matthew John Hurt, Thomas Edward BRINSON, Andrew James FLEMING, George Eugene WILMOT
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Publication number: 20180045068Abstract: The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.Type: ApplicationFiled: August 11, 2016Publication date: February 15, 2018Inventors: Thomas Edward Brinson, Paul Robert Gemin
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Publication number: 20160153359Abstract: Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.Type: ApplicationFiled: June 30, 2015Publication date: June 2, 2016Inventors: Kevin Richard Leamy, Benjamin Paul Breig, Michael Jay Epstein, Javier Armando Parrilla, Matthew John Hurt, Thomas Edward Brinson, Andrew James Fleming