Patents by Inventor Stuart Cooper
Stuart Cooper 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: 11280495Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.Type: GrantFiled: March 4, 2020Date of Patent: March 22, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Gurunath Gandikota, Steven Clayton Vise, Perumallu Vukanti, Mayank Krisna Amble, Clayton Stuart Cooper, Nicholas Ryan Overman, Karthikeyan Sampath, Allen Michael Danis, Craig Douglas Young
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Patent number: 11268438Abstract: An apparatus and method for a combustor, the combustor including combustor liner having a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and mixed with dilution air to form a flow of combustion gases. The flow of combustion gases travels through the combustor to a turbine section of an engine.Type: GrantFiled: September 15, 2017Date of Patent: March 8, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Steven Clayton Vise, Allen Michael Danis, Jayanth Sekar, Pradeep Naik, Perumallu Vukanti, Arthur Wesley Johnson, Clayton Stuart Cooper, Karthikeyan Sampath
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Publication number: 20210317990Abstract: Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.Type: ApplicationFiled: June 25, 2021Publication date: October 14, 2021Inventors: Gregory Allen Boardman, Michael Anthony Benjamin, Clayton Stuart Cooper, Joseph Zelina, Eric John Stevens
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Patent number: 11143106Abstract: The present disclosure is directed to a propulsion system including a wall defining a combustion chamber inlet, a combustion chamber outlet, and a combustion chamber therebetween, a nozzle assembly disposed at the combustion chamber inlet, the nozzle assembly configured to provide a fuel/oxidizer mixture to the combustion chamber, a turbine nozzle coupled to the wall and positioned at the combustion chamber outlet, wherein the turbine nozzle defines a cooling circuit within the turbine nozzle, and a casing positioned radially adjacent to the wall, wherein a channel structure is positioned between the casing and the wall, the channel structure in fluid communication with the cooling circuit within the turbine nozzle, and wherein a flowpath is formed between the wall and the casing, the flowpath in fluid communication from the cooling circuit at the turbine nozzle to the nozzle assembly to provide a flow of oxidizer to the thereto.Type: GrantFiled: November 6, 2019Date of Patent: October 12, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Joseph Zelina, Sibtosh Pal, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
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Patent number: 11131461Abstract: A method and system of effervescent atomization of liquid fuel for a rotating detonation combustor (RDC) for a propulsion system is provided. The method includes flowing liquid fuel through a fuel injection port of a nozzle assembly of the RDC system; flowing a gas through the fuel injection port of the nozzle assembly volumetrically proportional to the liquid fuel; producing a gas-liquid fuel mixture at the fuel injection port by mixing the flow of gas and the flow of liquid fuel; flowing an oxidizer through a nozzle flowpath of the RDC system; producing an oxidizer-gas-liquid fuel mixture by mixing the gas-liquid fuel mixture and the flow of oxidizer within the nozzle flowpath; and igniting the oxidizer-gas-liquid fuel mixture within a combustion chamber of the RDC system.Type: GrantFiled: December 2, 2019Date of Patent: September 28, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
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Publication number: 20210293412Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.Type: ApplicationFiled: March 10, 2021Publication date: September 23, 2021Inventors: Gregory Allen Boardman, Pradeep Naik, Joseph Zelina, Clayton Stuart Cooper
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Publication number: 20210278085Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.Type: ApplicationFiled: March 4, 2020Publication date: September 9, 2021Inventors: Gurunath Gandikota, Steven Clayton Vise, Perumallu Vukanti, Mayank Krisna Amble, Clayton Stuart Cooper, Nicholas Ryan Overman, Karthikeyan Sampath, Allen Michael Danis, Craig Douglas Young
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Patent number: 11073114Abstract: Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage.Type: GrantFiled: December 12, 2018Date of Patent: July 27, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Clayton Stuart Cooper, Joseph Zelina
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Patent number: 11073286Abstract: Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.Type: GrantFiled: September 20, 2017Date of Patent: July 27, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Michael Anthony Benjamin, Clayton Stuart Cooper, Joseph Zelina, Eric John Stevens
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Patent number: 10976052Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.Type: GrantFiled: October 25, 2017Date of Patent: April 13, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Joseph Zelina, Clayton Stuart Cooper
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Patent number: 10976053Abstract: A combustor assembly includes a volute wall extended annularly around a combustor centerline, extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline, and defining a combustion chamber therewithin, an annular inner wall extended at least partially along a lengthwise direction from the volute wall, an annular outer wall extended at least partially along the lengthwise direction from the volute wall, the annular inner wall and the annular outer wall being separated along a radial direction from the combustor centerline, and a primary flow passage being defined between the annular inner wall and the annular outer wall in fluid communication with the combustion chamber, and a flow passage wall extending between a portion of the volute wall and a portion of the annular outer wall.Type: GrantFiled: October 25, 2017Date of Patent: April 13, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Joseph Zelina, Clayton Stuart Cooper
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Patent number: 10935245Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline.Type: GrantFiled: November 20, 2018Date of Patent: March 2, 2021Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Manampathy Gangadharan Giridharan, Michael Anthony Benjamin, Pradeep Naik, Clayton Stuart Cooper, Vishal Sanjay Kediya
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Patent number: 10890327Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.Type: GrantFiled: February 14, 2018Date of Patent: January 12, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gurunath Gandikota, Hiranya Kumar Nath, Arvind Kumar Rao, Steven Clayton Vise, Perumallu Vukanti, Mayank Krisna Amble, Clayton Stuart Cooper
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Publication number: 20200393128Abstract: A propulsion system defining a longitudinal centerline extended along a longitudinal direction is provided. The propulsion system includes an inlet section configured to provide an oxidizer to a rotating detonation combustion system positioned downstream of the inlet section. The rotating detonation combustion system includes a nozzle assembly positioned to provide a flow mixture of oxidizer and fuel to a combustion chamber, a centerbody forming an inner wall of the combustion chamber, an outer wall at least partially surrounding the centerbody, wherein the inner wall and the outer wall define a volume of the combustion chamber; and an actuation structure coupled to the nozzle assembly. The actuation structure is configured to expand and contract to displace the nozzle assembly along the longitudinal direction to alter the volume of the combustion chamber.Type: ApplicationFiled: August 27, 2020Publication date: December 17, 2020Inventors: Joseph Zelina, Sibtosh Pal, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
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Patent number: 10837643Abstract: A mixer assembly for a turbine engine is generally provided. The mixer assembly includes a vane assembly including a plurality of vanes configured to direct a flow of oxidizer to mix with a flow of fuel. The vane assembly includes a fluid diode disposed within a vane flow path between each pair of vanes of the vane assembly.Type: GrantFiled: August 6, 2018Date of Patent: November 17, 2020Assignee: General Electric CompanyInventors: Sibtosh Pal, Clayton Stuart Cooper, Arthur Wesley Johnson, Steven Clayton Vise, Michael Anthony Benjamin, Allen Michael Danis
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Patent number: 10823422Abstract: A trapped vortex combustor for use in a gas turbine engine defines a radial direction, an axial direction, and a circumferential direction. The trapped vortex combustor includes an outer vortex chamber wall defining a forward end, and a dome attached to, or formed integrally with, the outer vortex chamber wall at the forward end of the outer vortex chamber wall. The dome and outer vortex chamber wall define at least in part a combustion chamber having an outer trapped vortex chamber. The dome includes an air chute defining an airflow direction. The radial direction and axial direction of the trapped vortex combustor define a reference plane extending through the air chute, the airflow direction of the air chute defining an angle greater than zero with the reference plane.Type: GrantFiled: October 17, 2017Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Arthur Wesley Johnson, Joseph Zelina, Eric John Stevens, Clayton Stuart Cooper, Beverly Stephenson Duncan, Juntao Zhang
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Patent number: 10724739Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.Type: GrantFiled: March 24, 2017Date of Patent: July 28, 2020Assignee: General Electric CompanyInventors: Kwanwoo Kim, Owen Graham, Clayton Stuart Cooper
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Publication number: 20200191093Abstract: Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage.Type: ApplicationFiled: December 12, 2018Publication date: June 18, 2020Inventors: Gregory Allen Boardman, Pradeep Naik, Clayton Stuart Cooper
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Publication number: 20200191101Abstract: Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage.Type: ApplicationFiled: December 12, 2018Publication date: June 18, 2020Inventors: Gregory Allen Boardman, Pradeep Naik, Clayton Stuart Cooper, Joseph Zelina
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Publication number: 20200158343Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline.Type: ApplicationFiled: November 20, 2018Publication date: May 21, 2020Inventors: Gregory Allen Boardman, Manampathy Gangadharan Giridharan, Michael Anthony Benjamin, Pradeep Naik, Clayton Stuart Cooper, Vishal Sanjay Kediya