Patents by Inventor Steven M. O'Flarity
Steven M. O'Flarity 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: 11982233Abstract: A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.Type: GrantFiled: October 28, 2022Date of Patent: May 14, 2024Assignee: RTX CORPORATIONInventor: Steven M. O'Flarity
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Publication number: 20230057875Abstract: A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.Type: ApplicationFiled: October 28, 2022Publication date: February 23, 2023Inventor: Steven M. O'Flarity
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Publication number: 20220412255Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.Type: ApplicationFiled: August 29, 2022Publication date: December 29, 2022Inventors: Steven M. O'Flarity, Neil Terwilliger
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Patent number: 11525402Abstract: A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.Type: GrantFiled: January 7, 2020Date of Patent: December 13, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Steven M. O'Flarity
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Patent number: 11428161Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.Type: GrantFiled: January 6, 2021Date of Patent: August 30, 2022Assignee: Raytheon Technologies CorporationInventors: Steven M. O'Flarity, Neil Terwilliger
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Publication number: 20210231051Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.Type: ApplicationFiled: January 6, 2021Publication date: July 29, 2021Inventors: Steven M. O'Flarity, Neil Terwilliger
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Publication number: 20210207538Abstract: A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.Type: ApplicationFiled: January 7, 2020Publication date: July 8, 2021Inventor: Steven M. O'Flarity
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Publication number: 20210054784Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.Type: ApplicationFiled: August 23, 2019Publication date: February 25, 2021Inventors: Steven M. O'Flarity, Neil Terwilliger
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Patent number: 10914234Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.Type: GrantFiled: August 23, 2019Date of Patent: February 9, 2021Assignee: Raytheon Technologies CorporationInventors: Steven M. O'Flarity, Neil Terwilliger
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Patent number: 10837359Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.Type: GrantFiled: February 27, 2017Date of Patent: November 17, 2020Assignee: Raytheon Technologies CorporationInventors: Gabriel L. Suciu, Michael E. McCune, Jesse M. Chandler, Alan H. Epstein, Steven M. O'Flarity, Christopher J. Hanlon, William F. Schneider, Joseph B. Staubach, James A. Kenyon
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Patent number: 10563616Abstract: A method of operating a gas turbine engine includes generating a flow of combustion products from a gas turbine generator that has a gas generator axis of rotation. A duct is oriented in a first position to direct the flow of combustion products that have passed over at least one gas generator turbine rotor through a fan drive turbine in response to a first desired flight condition. An axis of rotation of the fan drive turbine is transverse to a gas generator axis of rotation. The duct is oriented in a second position to direct the flow of combustion products that have passed over at least one gas generator turbine rotor through an augmentor section in response to a second desired flight condition.Type: GrantFiled: October 23, 2018Date of Patent: February 18, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Steven M. O'Flarity
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Patent number: 10421554Abstract: A drive arrangement for an aircraft comprises a pair of propulsor units each having a fan and a fan shaft for driving the fan. A core engine has a turbine driving a core engine shaft. A mechanical connection connects the core engine shaft to drive the fan shafts for each of the propulsor units. An aircraft also has such an arrangement.Type: GrantFiled: October 5, 2015Date of Patent: September 24, 2019Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Jesse M. Chandler, Wesley K. Lord, Alan H. Epstein, Steven M. O'Flarity
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Publication number: 20190113234Abstract: A method of operating a gas turbine engine includes generating a flow of combustion products from a gas turbine generator that has a gas generator axis of rotation. A duct is oriented in a first position to direct the flow of combustion products that have passed over at least one gas generator turbine rotor through a fan drive turbine in response to a first desired flight condition. An axis of rotation of the fan drive turbine is transverse to a gas generator axis of rotation. The duct is oriented in a second position to direct the flow of combustion products that have passed over at least one gas generator turbine rotor through an augmentor section in response to a second desired flight condition.Type: ApplicationFiled: October 23, 2018Publication date: April 18, 2019Inventor: Steven M. O'Flarity
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Patent number: 10107500Abstract: A gas turbine engine includes a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. There is a duct located downstream of the gas generator. The duct is configured to move between a first position and a second position. A fan drive turbine is positioned downstream of a path of the products of combustion and passes over at least one gas generator turbine rotor when the duct is in the first position. The fan drive turbine is for driving a shaft and the shaft is for engaging gears to drive at least two fan rotors. An augmentor section is positioned downstream of a path of products of combustion and passes over at least one gas generator turbine rotor when the duct is in second position.Type: GrantFiled: May 15, 2015Date of Patent: October 23, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Steven M. O'Flarity
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Publication number: 20170306842Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.Type: ApplicationFiled: February 27, 2017Publication date: October 26, 2017Inventors: Gabriel L. Suciu, Michael E. McCune, Jesse M. Chandler, Alan H. Epstein, Steven M. O'Flarity, Christopher J. Hanlon, William F. Schneider, Joseph B. Staubach, James A. Kenyon
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Patent number: 9650954Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.Type: GrantFiled: January 15, 2015Date of Patent: May 16, 2017Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Michael E. McCune, Jesse M. Chandler, Alan H. Epstein, Steven M. O'Flarity, Christopher J. Hanlon, William F. Schneider, Joseph B. Staubach, James A. Kenyon
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Publication number: 20170096232Abstract: A drive arrangement for an aircraft comprises a pair of propulsor units each having a fan and a fan shaft for driving the fan. A core engine has a turbine driving a core engine shaft. A mechanical connection connects the core engine shaft to drive the fan shafts for each of the propulsor units An aircraft is also disclosed.Type: ApplicationFiled: October 5, 2015Publication date: April 6, 2017Inventors: Gabriel L. Suciu, Jesse M. Chandler, Wesley K. Lord, Alan H. Epstein, Steven M. O'Flarity
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Publication number: 20160377295Abstract: A gas turbine engine includes a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. There is a duct located downstream of the gas generator. The duct is configured to move between a first position and a second position. A fan drive turbine is positioned downstream of a path of the products of combustion and passes over at least one gas generator turbine rotor when the duct is in the first position. The fan drive turbine is for driving a shaft and the shaft is for engaging gears to drive at least two fan rotors. An augmentor section is positioned downstream of a path of products of combustion and passes over at least one gas generator turbine rotor when the duct is in second position.Type: ApplicationFiled: May 15, 2015Publication date: December 29, 2016Inventor: Steven M. O'Flarity
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Publication number: 20150226117Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.Type: ApplicationFiled: January 15, 2015Publication date: August 13, 2015Inventors: Gabriel L. Suciu, Michael E. McCune, Jesse M. Chandler, Alan H. Epstein, Steven M. O'Flarity, Christopher J. Hanlon, William F. Schneider, Joseph B. Staubach, James A. Kenyon