Patents by Inventor Joseph Brent Staubach
Joseph Brent Staubach 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: 11976863Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.Type: GrantFiled: October 7, 2022Date of Patent: May 7, 2024Assignee: RTX CorporationInventors: Nathan Snape, Joseph Brent Staubach
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Patent number: 11787548Abstract: Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO2 (sCO2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO2 to mechanical energy to perform useful work onboard the aircraft.Type: GrantFiled: September 30, 2022Date of Patent: October 17, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Thomassin, Serge Dussault, Joseph Brent Staubach
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Publication number: 20230041007Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.Type: ApplicationFiled: October 7, 2022Publication date: February 9, 2023Inventors: Nathan Snape, Joseph Brent Staubach
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Publication number: 20230031511Abstract: Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO2 (sCO2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO2 to mechanical energy to perform useful work onboard the aircraft.Type: ApplicationFiled: September 30, 2022Publication date: February 2, 2023Inventors: Jean THOMASSIN, Serge DUSSAULT, Joseph Brent STAUBACH
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Patent number: 11549728Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.Type: GrantFiled: October 1, 2020Date of Patent: January 10, 2023Assignee: Raytheon Technologies CorporationInventors: Nathan Snape, Joseph Brent Staubach
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Patent number: 11485504Abstract: Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO2 (sCO2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO2 to mechanical energy to perform useful work onboard the aircraft.Type: GrantFiled: October 27, 2020Date of Patent: November 1, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Thomassin, Serge Dussault, Joseph Brent Staubach
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Publication number: 20220127009Abstract: Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO2 (sCO2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO2 to mechanical energy to perform useful work onboard the aircraft.Type: ApplicationFiled: October 27, 2020Publication date: April 28, 2022Inventors: Jean THOMASSIN, Serge DUSSAULT, Joseph Brent STAUBACH
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Patent number: 11215197Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.Type: GrantFiled: January 18, 2019Date of Patent: January 4, 2022Assignee: Raytheon Technologies CorporationInventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry
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Patent number: 10914242Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.Type: GrantFiled: November 28, 2017Date of Patent: February 9, 2021Assignee: Raytheon Technologies CorporationInventors: Joseph Brent Staubach, Nathan Snape, Frederick M. Schwarz, Charles E. Lents, Michael K. Ikeda
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Publication number: 20210018228Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.Type: ApplicationFiled: October 1, 2020Publication date: January 21, 2021Inventors: Nathan Snape, Joseph Brent Staubach
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Patent number: 10830148Abstract: A gas turbine engine includes a main compressor. A tap is fluidly connected downstream of the main compressor. A heat exchanger is fluidly connected downstream of the tap. An auxiliary compressor unit is fluidly connected downstream of the heat exchanger. The auxiliary compressor unit is configured to compress air cooled by the heat exchanger with an overall auxiliary compressor unit pressure ratio between 1.1 and 6.0. An intercooling system for a gas turbine engine is also disclosed.Type: GrantFiled: May 14, 2018Date of Patent: November 10, 2020Assignee: Raytheon Technologies CorporationInventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry, Wesley K. Lord
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Patent number: 10823462Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.Type: GrantFiled: September 19, 2016Date of Patent: November 3, 2020Assignee: Raytheon Technologies CorporationInventors: Nathan Snape, Joseph Brent Staubach
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Patent number: 10794290Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.Type: GrantFiled: November 8, 2017Date of Patent: October 6, 2020Assignee: Raytheon Technologies CorporationInventors: Nathan Snape, Joseph Brent Staubach, Frederick M. Schwarz
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Patent number: 10718268Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses cooling air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.Type: GrantFiled: November 9, 2017Date of Patent: July 21, 2020Assignee: Raytheon Technologies CorporationInventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry, Wesley K. Lord
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Patent number: 10480419Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passing the tapped air through a first heat exchanger and then to a cooling compressor. A second tap taps air from a location closer to the downstream most end than the location of the first tap, and the first and second taps mix together and are delivered into the high pressure turbine. The cooling compressor is positioned downstream of the first heat exchanger, and upstream of a location where air from the first and second taps mix together.Type: GrantFiled: June 22, 2015Date of Patent: November 19, 2019Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry
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Publication number: 20190323789Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.Type: ApplicationFiled: July 3, 2019Publication date: October 24, 2019Inventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry
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Patent number: 10371061Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.Type: GrantFiled: October 13, 2016Date of Patent: August 6, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Paul R. Adams, Shankar S. Magge, Joseph Brent Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
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Publication number: 20190162121Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.Type: ApplicationFiled: November 28, 2017Publication date: May 30, 2019Inventors: Joseph Brent Staubach, Nathan Snape, Frederick M. Schwarz, Charles E. Lents, Michael K. Ikeda
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Publication number: 20190154059Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.Type: ApplicationFiled: January 18, 2019Publication date: May 23, 2019Inventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry
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Patent number: 10221862Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.Type: GrantFiled: April 24, 2015Date of Patent: March 5, 2019Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry