Patents by Inventor Clayton S. Cooper

Clayton S. 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).

  • Patent number: 11906165
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
    Type: Grant
    Filed: April 11, 2022
    Date of Patent: February 20, 2024
    Assignee: General Electric Company
    Inventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
  • Publication number: 20240053013
    Abstract: A combustor for a turbine engine. The combustor includes a fuel injector and a fluid injection system in fluid communication with the combustor. The fuel injector includes a mixer assembly with a pilot mixer and a main mixer. The pilot mixer and the main mixer operate during high power operation of the turbine engine. The fluid injection system injects a fluid into the combustor during high power operation of the turbine engine. The fluid is shut off during low power operation of the turbine engine and during mid-level power operation of the turbine engine.
    Type: Application
    Filed: August 12, 2022
    Publication date: February 15, 2024
    Inventors: Joseph Zelina, Shai Birmaher, Sibtosh Pal, Clayton S. Cooper
  • Publication number: 20230366551
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
    Type: Application
    Filed: July 11, 2023
    Publication date: November 16, 2023
    Inventors: Perumallu Vukanti, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Michael T. Bucaro, Manampathy G. Giridharan, Steven C. Vise, Ajoy Patra, Saket Singh, R Narasimha Chiranthan
  • Publication number: 20230304665
    Abstract: A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.
    Type: Application
    Filed: April 18, 2023
    Publication date: September 28, 2023
    Inventors: Ajoy Patra, Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, R Narasimha Chiranthan, Manampathy G. Giridharan, Michael A. Benjamin, Clayton S. Cooper
  • Publication number: 20230296250
    Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.
    Type: Application
    Filed: May 10, 2022
    Publication date: September 21, 2023
    Inventors: Manampathy G. Giridharan, Michael T. Bucaro, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan
  • Patent number: 11725819
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
    Type: Grant
    Filed: February 28, 2022
    Date of Patent: August 15, 2023
    Assignee: General Electric Company
    Inventors: Perumallu Vukanti, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Michael T. Bucaro, Manampathy G. Giridharan, Steven C. Vise, Ajoy Patra, Saket Singh, R Narasimha Chiranthan
  • Publication number: 20230220998
    Abstract: A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.
    Type: Application
    Filed: March 15, 2022
    Publication date: July 13, 2023
    Inventors: Michael T. Bucaro, Clayton S. Cooper
  • Publication number: 20230220993
    Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor liner, a dome assembly coupled to the combustor liner, a fuel nozzle fluidly coupled to the dome assembly, a combustion chamber fluidly coupled to the fuel nozzle, and at least one set of dilution openings located in the dome assembly or combustor liner that fluidly couple to the combustion chamber. A swirler can define at least one passage extending between at least one annular entrance and at least one annular exit, wherein the at least one annular entrance is fluidly coupled to the compressor section. A variable area device is movable relative to the at least one set of dilution openings or at least a portion of the swirler.
    Type: Application
    Filed: March 4, 2022
    Publication date: July 13, 2023
    Inventors: Michael T. Bucaro, Clayton S. Cooper
  • Publication number: 20230204215
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.
    Type: Application
    Filed: February 18, 2022
    Publication date: June 29, 2023
    Inventors: Pradeep Naik, Ajoy Patra, Michael T. Bucaro, Perumallu Vukanti, Steven C. Vise, Michael A. Benjamin, Manampathy G. Giridharan, Saket Singh, Clayton S. Cooper
  • Publication number: 20230194093
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
    Type: Application
    Filed: April 11, 2022
    Publication date: June 22, 2023
    Inventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
  • Publication number: 20230194092
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and meeting emission needs can be met with the use of alternative fuels, which combust at higher temperatures or higher speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
    Type: Application
    Filed: February 28, 2022
    Publication date: June 22, 2023
    Inventors: Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, Steven C. Vise, Ajoy Patra, R Narasimha Chiranthan, Manampathy G. Giridharan, Michael A. Benjamin, Clayton S. Cooper, Dharmaraj Pachaiappan
  • Publication number: 20230194095
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and emission needs require the use of alternative fuels, which combust at higher temperatures and faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
    Type: Application
    Filed: March 22, 2022
    Publication date: June 22, 2023
    Inventors: Perumallu Vukanti, Pradeep Naik, Michael T. Bucaro, Ajoy Patra, Manampathy G. Giridharan, Steven C. Vise, R Narasimha Chiranthan, Michael A. Benjamin, Clayton S. Cooper
  • Publication number: 20230194091
    Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
    Type: Application
    Filed: February 28, 2022
    Publication date: June 22, 2023
    Inventors: Perumallu Vukanti, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Michael T. Bucaro, Manampathy G. Giridharan, Steven C. Vise, Ajoy Patra, Saket Singh, R Narasimha Chiranthan
  • Publication number: 20230194088
    Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.
    Type: Application
    Filed: March 4, 2022
    Publication date: June 22, 2023
    Inventors: Manampathy G. Giridharan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan
  • Patent number: 11649966
    Abstract: A turbine engine having a combustion section. The combustion section can have a combustor, at least one fuel cup, and at least one ignition tube. The combustor can include a combustor liner and a dome wall, which together at least partially define a combustion chamber. The at least one fuel cup can include a swirler and a fuel injector. The at least one ignition tube can include an outlet directly fluidly coupled to the combustion chamber.
    Type: Grant
    Filed: March 8, 2022
    Date of Patent: May 16, 2023
    Assignee: General Electric Company
    Inventors: Ajoy Patra, Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, R Narasimha Chiranthan, Manampathy G. Giridharan, Michael A. Benjamin, Clayton S. Cooper
  • Patent number: 11578869
    Abstract: A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.
    Type: Grant
    Filed: May 20, 2021
    Date of Patent: February 14, 2023
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Joseph Zelina, Clayton S. Cooper, Michael T. Bucaro, Steven C. Vise, John Thomas Herbon
  • Publication number: 20220412550
    Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.
    Type: Application
    Filed: August 6, 2021
    Publication date: December 29, 2022
    Inventors: Steven C. Vise, Clayton S. Cooper, Michael A. Benjamin, Pradeep Naik, Kwanwoo Kim, Shai Birmaher, Perumallu Vukanti, Saket Singh, Karthikeyan Sampath
  • Publication number: 20220372915
    Abstract: A gas turbine engine that is configured to mitigate fuel coupled dynamics. The engine includes a combustor, a fuel delivery system, a fuel manifold line; and a device configured to mitigate fuel coupled dynamics. The device is attached to the fuel manifold line and includes a housing and a reflector. The housing includes a wall and the wall defines a housing surface that is configured to reflect waves conducted by fuel within the fuel delivery system. The reflector is positioned within the housing and the reflector includes an anterior surface that is configured to reflect waves conducted by fuel within the fuel delivery system such that wave the reflected waves can strike the surface.
    Type: Application
    Filed: May 18, 2021
    Publication date: November 24, 2022
    Inventors: Gurunath Gandikota, Steven Clayton Vise, Clayton S. Cooper, Michael A. Benjamin
  • Publication number: 20220373181
    Abstract: A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.
    Type: Application
    Filed: May 20, 2021
    Publication date: November 24, 2022
    Inventors: Joseph Zelina, Clayton S. Cooper, Michael T. Bucaro, Steven C. Vise, John Thomas Herbon
  • Patent number: 11428411
    Abstract: A venturi for a swirler assembly of a combustor for a gas turbine engine. The venturi has an annular wall having internal diameter of a forward end of the annular wall that is larger than an internal diameter of a middle portion of the annular wall, which is smaller than an internal diameter of an aft end of the annular wall. The internal surface of the annular wall has a plurality of grooves extending in a longitudinal direction from the forward end of the annular wall to the aft end of the annular wall. The plurality of grooves are angled with respect to a centerline axis of the annular wall and may be spiraled about the internal surface of the annular wall.
    Type: Grant
    Filed: May 18, 2021
    Date of Patent: August 30, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sibtosh Pal, Clayton S. Cooper, Nicholas R. Overman, Steven C. Vise