Patents by Inventor Craig Heathco
Craig Heathco 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: 9915201Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.Type: GrantFiled: December 26, 2013Date of Patent: March 13, 2018Assignee: Rolls-Royce CorporationInventors: Michael Abraham Karam, Craig Heathco, Andrew Eifert
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Patent number: 9915202Abstract: An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.Type: GrantFiled: December 12, 2013Date of Patent: March 13, 2018Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Eric S. Donovan, Daniel J. Vonderwell, Craig Heathco
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Patent number: 9261019Abstract: One embodiment of the present invention is a unique variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for variable cycle gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: GrantFiled: December 27, 2011Date of Patent: February 16, 2016Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Craig Heathco
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Patent number: 9109539Abstract: An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.Type: GrantFiled: December 27, 2010Date of Patent: August 18, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Robert T. Duge, Craig Heathco, Brian Paul King
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Publication number: 20140356125Abstract: An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.Type: ApplicationFiled: December 12, 2013Publication date: December 4, 2014Applicant: Rolls-Royce North American Technologies, Inc.Inventors: Eric S. Donovan, Daniel J. Vonderwell, Craig Heathco
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Publication number: 20140248121Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.Type: ApplicationFiled: December 26, 2013Publication date: September 4, 2014Applicant: Rolls-Royce CorporationInventors: Michael Abraham KARAM, Craig HEATHCO, Andrew EIFERT
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Publication number: 20120233980Abstract: One embodiment of the present invention is a unique variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for variable cycle gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: December 27, 2011Publication date: September 20, 2012Inventor: Craig Heathco
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Publication number: 20120159925Abstract: An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.Type: ApplicationFiled: December 27, 2010Publication date: June 28, 2012Inventors: Robert T. Duge, Craig Heathco, Brian Paul King
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Patent number: 8186168Abstract: A method of at least partially balancing axial thrust loads and an engine in which the method is carried out is disclosed herein. The engine includes a combustion chamber and a fuel system operable to direct pressurized fuel to the combustion chamber. The engine also includes a rotor operable to rotate about a centerline axis and subjected to axial thrust loads during operation. The engine also includes a balance piston engaged with the rotor. The balance piston includes a pressure face positioned in a thrust cavity. The engine also includes a fluid passageway extending between the fuel system and the thrust cavity. Pressurized fuel is delivered to the pressure face to counteract axial thrust loads on the rotor.Type: GrantFiled: July 18, 2008Date of Patent: May 29, 2012Assignee: Rolls-Royce CorporationInventor: Craig Heathco
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Publication number: 20110154805Abstract: One embodiment of the present invention is a unique augmented gas turbine engine propulsion system. Another embodiment is a gas turbine engine power augmentation system. Yet another embodiment is a system for augmenting power in an engine powered air vehicle. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.Type: ApplicationFiled: December 21, 2010Publication date: June 30, 2011Inventors: Craig Heathco, Robert T. Duge, Steven Arlen Klusman
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Publication number: 20100014957Abstract: A method of at least partially balancing axial thrust loads and an engine in which the method is carried out is disclosed herein. The engine includes a combustion chamber and a fuel system operable to direct pressurized fuel to the combustion chamber. The engine also includes a rotor operable to rotate about a centerline axis and subjected to axial thrust loads during operation. The engine also includes a balance piston engaged with the rotor. The balance piston includes a pressure face positioned in a thrust cavity. The engine also includes a fluid passageway extending between the fuel system and the thrust cavity. Pressurized fuel is delivered to the pressure face to counteract axial thrust loads on the rotor.Type: ApplicationFiled: July 18, 2008Publication date: January 21, 2010Inventor: Craig Heathco