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).

  • Publication number: 20190101062
    Abstract: A system and method for operating a combustion system comprising a fuel nozzle defining at least one main fuel circuit and at least one pilot fuel circuit is generally provided. The method includes determining an overall flow of fuel, the overall flow of fuel defining a sum total fuel through the main fuel circuit and the pilot fuel circuit; determining a plurality of ranges of ratios of main fuel flow through the main fuel circuit versus pilot fuel flow through the pilot circuit from the overall flow of fuel, wherein each range of ratios is based on a combustion criterion different from one another; determining a resultant range of ratios of main fuel flow versus pilot fuel flow based on a hierarchy of combustion criteria, wherein the hierarchy of combustion criteria provides a priority ranking of the combustion criterion; and flowing the overall flow of fuel to the main fuel circuit and the pilot fuel circuit based on the resultant range of ratios of main fuel flow versus pilot fuel flow.
    Type: Application
    Filed: October 3, 2017
    Publication date: April 4, 2019
    Inventors: Steven Clayton Vise, Duane Douglas Thomsen, Richard Wade Stickles, Clayton Stuart Cooper, Donald Lee Gardner, George ChiaChun Hsiao, Michael Anthony Benjamin, Shai Birmaher
  • Publication number: 20190086092
    Abstract: 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: Application
    Filed: September 20, 2017
    Publication date: March 21, 2019
    Inventors: Gregory Allen Boardman, Michael Anthony Benjamin, Clayton Stuart Cooper, Joseph Zelina, Eric John Stevens
  • Publication number: 20190085767
    Abstract: 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: Application
    Filed: September 15, 2017
    Publication date: March 21, 2019
    Inventors: Steven Clayton Vise, Allen Michael Danis, Jayanth Sekar, Pradeep Naik, Perumallu Vukanti, Arthur Wesley Johnson, Clayton Stuart Cooper, Karthikeyan Sampath
  • Publication number: 20190024895
    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an inner liner and an outer liner together defining a combustion chamber therebetween and a pressure plenum surrounding the inner liner and the outer liner. One or more of the inner liner and the outer liner defines one or more openings. The one or more liners includes a walled chute disposed at least partially within the opening. A structural member extends from the one or more liners to the walled chute.
    Type: Application
    Filed: July 18, 2017
    Publication date: January 24, 2019
    Inventors: Richard Wade Stickles, Clayton Stuart Cooper, Perumallu Vukanti, Mayank Krisna Amble
  • Publication number: 20180363555
    Abstract: The present disclosure is directed to a propulsion system including an annular inner wall and an annular outer wall, a nozzle assembly, a turbine nozzle, and an inner casing and an outer casing. The inner wall and outer wall together extend at least partially along a longitudinal direction and together define a combustion chamber inlet, a combustion chamber outlet, and a combustion chamber therebetween. The nozzle assembly is disposed at the combustion inlet and provides a mixture of fuel and oxidizer to the combustion chamber. The turbine nozzle defines a plurality of airfoils in adjacent circumferential arrangement disposed at the combustion chamber outlet. The turbine nozzle is coupled to the outer wall and the inner wall. The inner casing is disposed inward of the inner wall and the outer casing is disposed outward of the outer wall. Each of the inner casing and the outer casing are coupled to the turbine nozzle.
    Type: Application
    Filed: June 15, 2017
    Publication date: December 20, 2018
    Inventors: Joseph Zelina, Sibtosh Pal, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Publication number: 20180355822
    Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system including a plurality of combustors in adjacent arrangement along the circumferential direction. Each combustor defines a combustor centerline extended through each combustor, and each combustor comprises an outer wall defining a combustion chamber and a combustion inlet. Each combustion chamber is defined by an annular gap and a combustion chamber length together defining a volume of each combustion chamber. Each combustor defines a plurality of nozzle assemblies each disposed at the combustion inlet in adjacent arrangement around each combustor centerline. Each nozzle assembly defines a nozzle wall extended along a lengthwise direction, a nozzle inlet, a nozzle outlet, and a throat therebetween, and each nozzle assembly defines a converging-diverging nozzle. A first array of combustors defines a first volume and a second array of combustors defines a second volume different from the first volume.
    Type: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Steven Clayton Vise, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Sibtosh Pal
  • Publication number: 20180356099
    Abstract: The present disclosure is directed to a propulsion system including a rotating detonation combustion (RDC) system defining a plurality of fuel-oxidizer mixing nozzles each defined by a converging-diverging nozzle wall defining a nozzle flowpath. The nozzle wall defines a throat and a lengthwise direction extended between a nozzle inlet and nozzle outlet along the lengthwise direction. The longitudinal centerline of the propulsion system and the radial direction together define a reference plane, and the lengthwise direction of the nozzle intersects the reference plane and defines a nozzle angle greater than zero degrees and approximately 80 degrees or less relative to the reference plane.
    Type: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Joseph Zelina, Sibtosh Pal, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Publication number: 20180356093
    Abstract: The present disclosure is directed to a method of operating a propulsion system including a rotating detonation combustion (RDC) system. The RDC system defines a combustion inlet at an upstream end, a combustion outlet at a downstream end, a combustion chamber therebetween, and a nozzle defined at the combustion inlet upstream of the combustion chamber, and a secondary flowpath extended from upstream of the nozzle to downstream of the nozzle.
    Type: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Sibtosh Pal, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Publication number: 20180355792
    Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system, the rotating detonation combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The rotating detonation combustion system includes an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining at least in part a combustion chamber and a combustion chamber inlet. The outer wall and the inner wall together define an annular nozzle concentric to the longitudinal centerline at the combustion chamber inlet. The nozzle defines a lengthwise direction and extending between a nozzle inlet and a nozzle outlet along the lengthwise direction, the nozzle inlet configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and nozzle outlet.
    Type: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Sibtosh Pal, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Publication number: 20180355793
    Abstract: A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle.
    Type: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Steven Clayton Vise, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Sibtosh Pal
  • Publication number: 20180356096
    Abstract: 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: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Sibtosh Pal, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Publication number: 20180355795
    Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system, the rotating detonation combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction.
    Type: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Sibtosh Pal, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Publication number: 20180356094
    Abstract: The present disclosure is directed to a method of operating a propulsion system at an approximately constant detonation cell quantity in the combustion chamber of a detonation combustion system. The propulsion system defines an inlet section upstream of the rotating detonation combustion system and an exhaust section downstream of the rotating detonation combustion system.
    Type: Application
    Filed: June 9, 2017
    Publication date: December 13, 2018
    Inventors: Joseph Zelina, Sibtosh Pal, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Publication number: 20180274780
    Abstract: 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: Application
    Filed: March 24, 2017
    Publication date: September 27, 2018
    Inventors: Kwanwoo Kim, Owen Graham, Clayton Stuart Cooper
  • Publication number: 20180104554
    Abstract: A golf putter including a putter head having a body portion and a reversible face. The golf putter further includes a hosel received by the body portion of the putter head and a shaft attachable to the hosel. A site alignment member is coupled to a surface of the body portion. The site alignment member may include one or more alignment markings for facilitating alignment of the golf club head during use.
    Type: Application
    Filed: October 11, 2017
    Publication date: April 19, 2018
    Inventors: Vikash Sanyal, David Stuart Cooper, JR., Jeffrey D. Sheets
  • Patent number: D799386
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: October 10, 2017
    Assignee: GM Global Technology Operations LLC
    Inventors: Timothy P. Kozub, Stuart Cooper, Jonghyuk Park
  • Patent number: D801236
    Type: Grant
    Filed: October 26, 2015
    Date of Patent: October 31, 2017
    Assignee: GM Global Technology Operations LLC
    Inventors: Timothy P. Kozub, Stuart Cooper, Jonghyuk Park
  • Patent number: D801882
    Type: Grant
    Filed: October 26, 2015
    Date of Patent: November 7, 2017
    Assignee: GM Global Technology Operations LLC
    Inventors: Timothy P. Kozub, Stuart Cooper, Jonghyuk Park
  • Patent number: D837109
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: January 1, 2019
    Assignee: GM Global Technology Operations LLC
    Inventors: Timothy P. Kozub, Stuart Cooper, Jonghyuk Park
  • Patent number: D841527
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: February 26, 2019
    Assignee: GM Global Technology Operations LLC
    Inventors: Timothy P. Kozub, Stuart Cooper, Jonghyuk Park