Patents by Inventor Scott David Hunter
Scott David Hunter 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: 11788465Abstract: A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.Type: GrantFiled: January 19, 2022Date of Patent: October 17, 2023Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Patrick Michael Marrinan, Arthur William Sibbach, Scott Alan Schimmels, Scott David Hunter
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Publication number: 20230228214Abstract: A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.Type: ApplicationFiled: January 19, 2022Publication date: July 20, 2023Inventors: Brandon Wayne Miller, Scott David Hunter, Patrick Michael Marrinan, Scott Alan Schimmels
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Publication number: 20230228213Abstract: A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.Type: ApplicationFiled: January 19, 2022Publication date: July 20, 2023Inventors: Brandon Wayne Miller, Patrick Michael Marrinan, Arthur William Sibbach, Scott Alan Schimmels, Scott David Hunter
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Publication number: 20230228216Abstract: A gas turbine engine may include a turbomachine defining a core flow having a core mass flow rate therethrough during operation. A bleed assembly is provided to include a bleed flow machine and a machine load. The bleed flow machine is provided in fluid communication with the compressor section of the turbomachine and configured to drive the machine load. A machine outlet in fluid communication with the bleed assembly provides a bleed flow therethrough during operation of the gas turbine engine, the bleed flow defining a bleed mass flow rate. A compressor section of the turbomachine is configured to provide the bleed flow through the bleed flow machine and the machine outlet to an aircraft flow assembly, wherein the bleed mass flow rate is at least twelve percent (12%) of the core mass flow rate.Type: ApplicationFiled: January 19, 2022Publication date: July 20, 2023Inventors: Brandon Wayne Miller, Scott David Hunter, Patrick Michael Marrinan, Scott Alan Schimmels
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Publication number: 20230228231Abstract: A gas turbine engine includes a turbomachine defining a core flow therethrough during operation. A first flow tap is configured to receive a first bleed flow from upstream of the combustion section. A second flow tap is configured to receive a second bleed flow from downstream of the combustion section. A first flow outlet is provided in fluid communication with the first flow tap and a second flow outlet is provided in fluid communication with the second flow tap. The first flow outlet and the second flow outlet are configured to direct the first bleed flow and the second bleed flow to at least one aircraft flow assembly.Type: ApplicationFiled: January 19, 2022Publication date: July 20, 2023Inventors: Brandon Wayne Miller, Scott David Hunter, Scott Alan Schimmels, Patrick Michael Marrinan
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Patent number: 11092013Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: GrantFiled: December 28, 2018Date of Patent: August 17, 2021Assignee: General Electric CompanyInventors: John Joseph Rahaim, Daniel John Fusinato, Scott David Hunter, Joel Francis Kirk, Michael Robert Melzak, Curtis Walton Stover
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Publication number: 20190136714Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: ApplicationFiled: December 28, 2018Publication date: May 9, 2019Inventors: John Joseph RAHAIM, Daniel John FUSINATO, Scott David HUNTER, Joel Francis KIRK, Michael Robert MELZAK, Curtis Walton STOVER
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Patent number: 10202867Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: GrantFiled: March 14, 2014Date of Patent: February 12, 2019Assignee: General Electric CompanyInventors: John Joseph Rahaim, Daniel John Fusinato, Scott David Hunter, Joel Francis Kirk, Michael Robert Melzak, Curtis Walton Stover
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Publication number: 20160040552Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers , the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: ApplicationFiled: March 14, 2014Publication date: February 11, 2016Inventors: John Joseph RAHAIM, Daniel John FUSINATO, Scott David HUNTER, Joel Francis KIRK, Michael Robert MELZAK, Curtis Walton STOVER
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Patent number: 7578653Abstract: A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.Type: GrantFiled: December 19, 2006Date of Patent: August 25, 2009Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Ching-Pang Lee, Scott David Hunter
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Publication number: 20080145216Abstract: A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.Type: ApplicationFiled: December 19, 2006Publication date: June 19, 2008Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Scott David Hunter
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Publication number: 20080145208Abstract: A turbine stage includes a stator nozzle cooperating with a row of turbine blades. The nozzle includes a row of vanes mounted between inner and outer bands, with the inner band adjoining the blades at inner platforms thereof at a rotary seal. The inner band includes a stator bullnose at the trailing edge thereof cooperating with the rotary seal for reducing aerodynamic losses thereat.Type: ApplicationFiled: December 19, 2006Publication date: June 19, 2008Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Scott David Hunter