Patents by Inventor Nathan Snape
Nathan Snape 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: 20240125564Abstract: A method can comprise dividing a heat exchanger design into a plurality of modules, the plurality of modules arranged in a grid, each module in the plurality of modules including: a first fluid conduit defining an inlet, an outlet, and a heat-transfer surface, and a first flow direction, and a second fluid conduit defining a second inlet, a second outlet, a second heat-transfer surface, and a second flow direction, the second flow direction different from the first flow direction; and determining a heat-transfer augmenter arrangement for the first fluid conduit and the second fluid conduit of each module in the plurality of modules based on a stress threshold of the module in the plurality of modules.Type: ApplicationFiled: October 14, 2022Publication date: April 18, 2024Applicant: Raytheon Technologies CorporationInventors: Isabella Snyder, David W Gerlach, Nathan A Snape
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Publication number: 20240102417Abstract: A gas turbine engine assembly including a tap that is at a location up stream of the combustor section for drawing a bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow and communicate the heated bleed airflow into the turbine section where it is expanded to drive the turbine section.Type: ApplicationFiled: September 23, 2022Publication date: March 28, 2024Inventors: Stephen H. Taylor, Alan Retersdorf, Oliver V. Atassi, Nathan A. Snape
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Publication number: 20240084731Abstract: A gas turbine engine assembly includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section through an engine drive shaft. A tap is at a location up stream of the combustor section for drawing a bleed airflow. A bleed air heat exchanger places the bleed airflow in thermal communication with an auxiliary flow for heating the bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow.Type: ApplicationFiled: September 6, 2023Publication date: March 14, 2024Inventors: Alan Retersdorf, Stephen H. Taylor, Nathan A. Snape, Oliver V. Atassi, Malcolm P. MacDonald
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Publication number: 20240076999Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.Type: ApplicationFiled: November 9, 2023Publication date: March 7, 2024Inventors: Frederick M. Schwarz, Nathan Snape
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Patent number: 11920485Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.Type: GrantFiled: August 15, 2022Date of Patent: March 5, 2024Assignee: RTX CorporationInventors: Frederick M. Schwarz, Nathan Snape
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Patent number: 11920526Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path where a core flow is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section. A fuel system is configured to supply a hydrogen based fuel to the combustor through a fuel flow path. A condenser is arranged along the core flow path and configured to extract water from the gas flow. An intercooling system receives a portion of water from the condenser for cooling a portion of the core flow at a first location within the compressor section. Heated water from the intercooling system is exhausted to a second location within the core flow path downstream of the first location.Type: GrantFiled: August 12, 2022Date of Patent: March 5, 2024Assignee: RTX CORPORATIONInventors: Neil J. Terwilliger, Nathan A. Snape, Joseph B. Staubach
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Publication number: 20240052792Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path where a core flow is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section. A fuel system is configured to supply a hydrogen based fuel to the combustor through a fuel flow path. A condenser is arranged along the core flow path and configured to extract water from the gas flow. An intercooling system receives a portion of water from the condenser for cooling a portion of the core flow at a first location within the compressor section. Heated water from the intercooling system is exhausted to a second location within the core flow path downstream of the first location.Type: ApplicationFiled: August 12, 2022Publication date: February 15, 2024Inventors: Neil J. Terwilliger, Nathan A. Snape, Joseph B. Staubach
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Patent number: 11808210Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A tap connects to the compressor section. A heat exchanger connects downstream of the tap. A cooling compressor connects downstream of the heat exchanger, and the cooling compressor connects to deliver air to at least one of the rotating components. A core housing has an outer peripheral surface and a fan housing defines an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is disposed within the at least one bifurcation duct.Type: GrantFiled: May 14, 2018Date of Patent: November 7, 2023Assignee: RTX CORPORATIONInventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry, Nathan Snape
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Publication number: 20230303254Abstract: A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.Type: ApplicationFiled: December 16, 2022Publication date: September 28, 2023Inventors: Frederick M. Schwarz, Michael Winter, Charles E. Lents, Nathan Snape, Alan H. Epstein
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Patent number: 11719169Abstract: A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.Type: GrantFiled: April 14, 2022Date of Patent: August 8, 2023Assignee: Raytheon Technologies CorporationInventors: Frederick M. Schwarz, Nathan A. Snape
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Publication number: 20230122852Abstract: An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.Type: ApplicationFiled: December 16, 2022Publication date: April 20, 2023Inventors: Frederick M. Schwarz, Michael Winter, Charles E. Lents, Nathan Snape, Alan H. Epstein
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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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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: 11542016Abstract: A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.Type: GrantFiled: March 21, 2019Date of Patent: January 3, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Frederick M. Schwarz, Michael Winter, Charles E. Lents, Nathan Snape, Alan H. Epstein
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Publication number: 20220389836Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.Type: ApplicationFiled: August 15, 2022Publication date: December 8, 2022Inventors: Frederick M. Schwarz, Nathan Snape
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Patent number: 11428121Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.Type: GrantFiled: April 5, 2019Date of Patent: August 30, 2022Assignee: Raytheon Technologies CorporationInventors: Frederick M. Schwarz, Nathan Snape
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Publication number: 20220243665Abstract: A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.Type: ApplicationFiled: April 14, 2022Publication date: August 4, 2022Inventors: Frederick M. Schwarz, Nathan A. Snape
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Patent number: 11346288Abstract: A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.Type: GrantFiled: September 21, 2016Date of Patent: May 31, 2022Assignee: Raytheon Technologies CorporationInventors: Frederick M. Schwarz, Nathan Snape
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Patent number: 11236675Abstract: A gas turbine engine has a compressor section with a downstream most end and a cooling air tap at a location spaced upstream from the downstream most end. The cooling air tap is passed through at least one boost compressor and at least one heat exchanger, and then passed to a turbine section to cool the turbine section. The boost compressor is driven by a driveshaft which is driven by the turbine section. A boost turbine selectively drives the boost compressor.Type: GrantFiled: March 17, 2020Date of Patent: February 1, 2022Assignee: Raytheon Technologies CorporationInventor: Nathan Snape
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Patent number: 11203976Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.Type: GrantFiled: February 24, 2020Date of Patent: December 21, 2021Assignee: Raytheon Technologies CorporationInventors: Vito Guardi, Christopher B. Lyons, Nathan Snape