Patents by Inventor William G. Cummings, III
William G. Cummings, III 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: 6238206Abstract: A burner (10) for use in both high O2 environments and low O2 environments comprises an outer tube (24) and an inner tube (26). The outer tube (24) defines a flow passage (53) and includes an inlet portion (42), an outlet portion (46), and a nozzle portion (44) interconnecting the inlet portion (42) and outlet portion (46). The inlet portion (42) has a larger effective cross-sectional area than the outlet portion (46) so that air (20) or an air-and-fuel mixture (35) moving through nozzle portion (44) is accelerated. The inner tube (26) is positioned to lie in the flow passage (53) of the outer tube (24) and is formed to include fuel-injection holes (78) to conduct fuel (33) into the flow passage (53).Type: GrantFiled: May 16, 2000Date of Patent: May 29, 2001Assignee: Maxon CorporationInventors: William G. Cummings, III, Curtis L. Taylor
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Patent number: 6059566Abstract: A burner apparatus is provided in accordance with the present invention that includes a case coupled to an air supply and a nozzle positioned to lie in case and coupled to a fuel supply. Nozzle defines at least one air-flow cavity inside case. Nozzle is formed to include a fuel-distribution chamber and at least one fuel-discharge port to communicate fuel from fuel-distribution chamber into air passing from air supply through each air-flow cavity. Fuel) mixes with air in each air-flow cavity to produce a combustible air-and-fuel mixture therein which can be ignited to produce a flame in case.Type: GrantFiled: July 24, 1998Date of Patent: May 9, 2000Assignee: Maxon CorporationInventor: William G. Cummings, III
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Patent number: 5344308Abstract: A combustion noise suppression system for a combustor assembly includes a number of holes formed in the combustor housing at a distance from the location at which an air and fuel mixture is introduced into the housing and ignited to produce flame.Type: GrantFiled: April 27, 1993Date of Patent: September 6, 1994Assignee: Maxon CorporationInventor: William G. Cummings, III
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Patent number: 5236350Abstract: A nozzle is provided for discharging a combustible air and fuel mixture into the combustion chamber of a cyclonic combustor. The nozzle includes a centrally located air plenum and a plurality of passageways for discharging air from the plenum into the combustion chamber. The nozzle also includes a fuel jet system for discharging fuel into each air discharge passageway to mix with the combustion air passing therethrough.Type: GrantFiled: November 15, 1991Date of Patent: August 17, 1993Assignee: Maxon CorporationInventors: William G. Cummings, III, William P. Coppin, David A. Jarvis
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Patent number: D322704Type: GrantFiled: April 6, 1990Date of Patent: December 24, 1991Assignee: Looker, Inc.Inventor: William G. Cummings, III