Patents by Inventor William G. Cummings
William G. Cummings 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: 11274829Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.Type: GrantFiled: September 20, 2019Date of Patent: March 15, 2022Assignee: Rolls-Royce CorporationInventors: Charles B. Graves, Russell N. Bennett, William G. Cummings, III, Jun Shi
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Publication number: 20200033005Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.Type: ApplicationFiled: September 20, 2019Publication date: January 30, 2020Inventors: Charles B. Graves, Russell N. Bennett, William G. Cummings, III, Jun Shi
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Patent number: 10458652Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.Type: GrantFiled: July 25, 2016Date of Patent: October 29, 2019Assignee: Rolls-Royce CorporationInventors: Charles B. Graves, Russell N. Bennett, William G. Cummings, III, Jun Shi
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Patent number: 10228139Abstract: A method for operating a gas turbine engine during flight operation of the gas turbine engine in an aircraft may include measuring a gas temperature downstream of the combustor using a plurality of temperature measurement devices circumferentially disposed about an engine centerline and varying the output of at least one fuel injector in a first direction and the output of at least another fuel injector in a second direction, while maintaining a thrust output of the gas turbine engine during the flight operation. A gas turbine engine may include temperature measurement devices circumferentially disposed about an engine centerline and a system configured for varying the output of at least one fuel injector in a first direction and the output of at least another fuel injector in a second direction, while maintaining a power output of the gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines.Type: GrantFiled: December 20, 2013Date of Patent: March 12, 2019Assignee: Rolls-Royce CorporationInventor: William G. Cummings, III
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Patent number: 10151243Abstract: A gas turbine engine includes a compressor, a turbine, and a combustor. The combustor includes a fuel injector and a vaporizer within the combustor positioned to receive liquid fuel from the fuel injector to vaporize the liquid fuel therein. The gas turbine engine includes an enclosed passage external to the combustor having a wall, a diffuser positioned to direct the air into the passage, causing the air to cool by transferring heat through the wall from the air within the passage to the vaporized fuel within the vaporizer, and a cooled cooling air passageway positioned to receive the air from the passage and direct the air after being cooled to at least one of the turbine and the compressor.Type: GrantFiled: March 4, 2016Date of Patent: December 11, 2018Assignee: Rolls-Royce CorporationInventors: Duane A. Smith, William G. Cummings, III
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Publication number: 20170146241Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.Type: ApplicationFiled: July 25, 2016Publication date: May 25, 2017Inventors: Charles B. Graves, Russell N. Bennett, William G. Cummings, III, Jun Shi
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Patent number: 9651258Abstract: A combustor for use in a gas turbine engine includes a liner with a plurality of tiles coupled to a shell via a plurality of fasteners. Each of the plurality of fasteners extends through at least one of the tiles.Type: GrantFiled: December 19, 2013Date of Patent: May 16, 2017Assignee: Rolls-Royce CorporationInventors: Charles B. Graves, William G. Cummings, III, Russell N. Bennett, Jun Shi
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Patent number: 9458768Abstract: A method including providing a wet algae material having been subjected to a refinement process without a water separation phase; supplying the wet algae material including a water fraction and an algae-grown biofuel to a turbine engine; and operating the turbine engine with the wet algae material where a retained portion of the water fraction is retained in the wet biofuel during a manufacturing process not including a dehydration step and includes an amount sufficient to reduce generation of a quantity of nitrogen oxides, and where the turbine engine can further include a combustor capable of combusting the wet biofuel.Type: GrantFiled: December 27, 2013Date of Patent: October 4, 2016Assignee: Rolls-Royce CorporationInventors: William G. Cummings, III, Enrico Lo Gatto
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Patent number: 9423129Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.Type: GrantFiled: December 19, 2013Date of Patent: August 23, 2016Assignee: Rolls-Royce CorporationInventors: Charles B Graves, William G Cummings, III, Russell N Bennett, Jun Shi
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Publication number: 20160186661Abstract: A gas turbine engine includes a compressor, a turbine, and a combustor. The combustor includes a fuel injector and a vaporizer within the combustor positioned to receive liquid fuel from the fuel injector to vaporize the liquid fuel therein. The gas turbine engine includes an enclosed passage external to the combustor having a wall, a diffuser positioned to direct the air into the passage, causing the air to cool by transferring heat through the wall from the air within the passage to the vaporized fuel within the vaporizer, and a cooled cooling air passageway positioned to receive the air from the passage and direct the air after being cooled to at least one of the turbine and the compressor.Type: ApplicationFiled: March 4, 2016Publication date: June 30, 2016Applicant: Rolls-Royce CorporationInventors: Duane A. Smith, William G. Cummings, III
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Publication number: 20150330633Abstract: A combustor for use in a gas turbine engine includes a liner with a plurality of tiles coupled to a shell via a plurality of fasteners. Each of the plurality of fasteners extends through at least one of the tiles.Type: ApplicationFiled: December 19, 2013Publication date: November 19, 2015Inventors: Charles B. Graves, William G. Cummings, III, Russell N. Bennett, Jun Shi
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Publication number: 20150000291Abstract: A gas turbine engine having a combustor is disclosed in which a heat exchanger is disposed within the combustor. The heat exchanger can take the form of a fuel/air heat exchanger. In one form the heat exchanger includes a path for cooling air to be conveyed to a location external to the combustor. Cooled cooling air carried through the path can be created through action of heat transfer from the cooling air to a fuel flowing in the heat exchanger. The heat exchanger can include a fuel vaporizer in one form.Type: ApplicationFiled: December 17, 2013Publication date: January 1, 2015Applicant: Rolls-Royce CorporationInventors: Duane A. Smith, William G. Cummings, III
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Publication number: 20140360196Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.Type: ApplicationFiled: December 19, 2013Publication date: December 11, 2014Inventors: Charles B. Graves, William G. Cummings, III, Russell N. Bennett, Jun Shi
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Publication number: 20140260304Abstract: A method including providing a wet algae material having been subjected to a refinement process without a water separation phase; supplying the wet algae material including a water fraction and an algae-grown biofuel to a turbine engine; and operating the turbine engine with the wet algae material where a retained portion of the water fraction is retained in the wet biofuel during a manufacturing process not including a dehydration step and includes an amount sufficient to reduce generation of a quantity of nitrogen oxides, and where the turbine engine can further include a combustor capable of combusting the wet biofuel.Type: ApplicationFiled: December 27, 2013Publication date: September 18, 2014Applicant: ROLLS-ROYCE CORPORATIONInventors: William G. CUMMINGS, III, Enrico LO GATTO
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Publication number: 20140238037Abstract: One embodiment of the present disclosure is a unique method for operating a gas turbine engine during flight operation of the gas turbine engine in an aircraft. Another embodiment of the present disclosure is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for 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 20, 2013Publication date: August 28, 2014Applicant: Rolls-Royce CorporationInventor: William G. Cummings, III
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Patent number: 8590313Abstract: A precision counter-swirl combustor that includes an annular combustor having a forward end, an aft end opposite the forward end, and an interior. The aft end being proximal to a gas turbine. The combustor further includes a fuel inlet and swirler operatively connected to the forward end and at least one air inlet. The air inlet is equipped with a chute that extends into the interior of said combustor. The combustor is secured to a fixed structure proximate the forward end of the combustor.Type: GrantFiled: July 30, 2008Date of Patent: November 26, 2013Assignee: Rolls-Royce CorporationInventors: Charles B. Graves, William G. Cummings
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Publication number: 20100024427Abstract: A precision counter-swirl combustor that includes an annular combustor having a forward end, an aft end opposite the forward end, and an interior. The aft end being proximal to a gas turbine. The combustor further includes a fuel inlet and swirler operatively connected to the forward end and at least one air inlet. The air inlet is equipped with a chute that extends into the interior of said combustor. The combustor is secured to a fixed structure proximate the forward end of the combustor.Type: ApplicationFiled: July 30, 2008Publication date: February 4, 2010Applicant: ROLLS-ROYCE CORPORATIONInventors: CHARLES B. GRAVES, William G. Cummings
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Patent number: 6474927Abstract: A freight transportation container can accept standardized pallets and is suitable for the transportation by land, sea, or air. The size and construction of the container permits the loading and removal of freight by a conventional fork lift truck, and allows placement of the container in standard-sized trucks and aircraft. Lockdown lips formed on the bottom of the container secure the container to the floors of trucks and aircraft. The freight container also is part of a system for transportation whereby the freight can be loaded, inventoried, locked, and sealed at a customer's premises, and remain under the custody of one entity throughout shipment of the freight to the consignee. An empty freight container can be delivered to a customer's premises on a truck having a cab and removable trailer, so that the container and trailer can remain there for loading, and then later be picked up by the cab and taken to holding areas, other trucks, ships, aircraft, or directly to the consignee.Type: GrantFiled: October 11, 1996Date of Patent: November 5, 2002Assignee: Federal Express CorporationInventors: Allen C. McAdams, Bruce Thomas Bullion, III, William G. Cummings, James Harold Idell, Barry J. Atkins, Mark D. Yerger
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Patent number: 6474006Abstract: An athletic shoe is provided which contributes to dynamic stability of the shoe during several athletic activities. The athletic shoe comprises a tapered lateral wedge section and may further include a lateral heel stabilizer, a medial heel wedge and a tapered lateral forefoot section.Type: GrantFiled: July 17, 2000Date of Patent: November 5, 2002Inventors: William G. Cummings, Jay G. Levine
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Patent number: RE40215Abstract: An athletic shoe is provided which contributes a dynamic stability of the shoe during several athletic activities. The athletic shoe comprises a tapered lateral wedge section and may further include a lateral heel stabilizer, a medial heel wedge and a tapered lateral forefoot section.Type: GrantFiled: October 27, 2004Date of Patent: April 8, 2008Inventors: William G. Cummings, Jay G. Levine