Patents by Inventor Michael A. Benjamin

Michael A. Benjamin 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: 11898755
    Abstract: A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.
    Type: Grant
    Filed: June 8, 2022
    Date of Patent: February 13, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Ravindra Shankar Ganiger, Hiranya Nath, Michael A. Benjamin, Nicholas R. Overman
  • Patent number: 11898752
    Abstract: A hollow plank of a combustor liner defining a combustion chamber including an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of lateral walls coupled to the inner wall and the outer wall to define a cavity, and a partition wall connected to the plurality of lateral walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The one or more outer openings communicate with the first sub-cavity and communicate through a plurality of tubes with the second sub-cavity. The plurality of inner openings communicate with the second sub-cavity and communicate with the first sub-cavity through one or more bypass tubes. The first sub-cavity or the second sub-cavity, or both, are frequency tuned to reduce combustion dynamic frequencies.
    Type: Grant
    Filed: September 15, 2022
    Date of Patent: February 13, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Hiranya Nath, Ravindra Shankar Ganiger, Michael A. Benjamin
  • Publication number: 20240044290
    Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system can be controlled to adjust one or more parameters of the fuel based on data received from the sensors.
    Type: Application
    Filed: October 18, 2023
    Publication date: February 8, 2024
    Applicant: General Electric Company
    Inventors: Brandon W. Miller, Robert Jon McQuiston, Stefan Joseph Cafaro, Eric Richard Westervelt, Michael A. Benjamin, Joel M. Haynes, Hejie Li
  • Patent number: 11892165
    Abstract: A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.
    Type: Grant
    Filed: May 19, 2021
    Date of Patent: February 6, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Hiranya Nath, Michael A. Benjamin, Rajendra Wankhade, Hari Chandra
  • Publication number: 20230408098
    Abstract: A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.
    Type: Application
    Filed: May 25, 2022
    Publication date: December 21, 2023
    Inventors: Saket Singh, Rimple Rangrej, Pradeep Naik, Michael A. Benjamin, Joseph Zelina
  • Publication number: 20230400187
    Abstract: A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.
    Type: Application
    Filed: June 8, 2022
    Publication date: December 14, 2023
    Inventors: Ravindra Shankar Ganiger, Hiranya Nath, Michael A. Benjamin, Nicholas R. Overman
  • Publication number: 20230400186
    Abstract: A mixing assembly includes a pilot mixer and a main mixer. The main mixer includes a main housing, a fuel manifold positioned between a pilot housing and the main housing, a mixer foot extending outward from a forward end of the main housing, and a main swirler body including a plurality of vanes. The main swirler body surrounds the main housing and defines an annular mixing channel between the main housing and the main swirler body, and being coupled to the mixer foot. An annular main fuel ring extends axially aft from the mixer foot into the annular mixing channel. The mixer foot extends farther from the main housing than the main fuel ring. At least one of the mixer foot or the main fuel ring includes a plurality of fuel injection ports positioned to discharge fuel into a central portion of the annular mixing channel.
    Type: Application
    Filed: August 16, 2023
    Publication date: December 14, 2023
    Inventors: Hari Ravi Chandra, Arvind Kumar Rao, Shai Birmaher, Jayanth Sekar, Gurunath Gandikota, Michael A. Benjamin
  • Publication number: 20230399980
    Abstract: A gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. The combustor includes a combustion chamber. The plurality of fuel injects fuel into the combustion chamber of the combustor. The gas turbine engine may include a first fuel circuit and a second fuel circuit. The first fuel circuit includes a first fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a first temperature. The second fuel circuit includes a second fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a second. The second temperature is less than the first temperature.
    Type: Application
    Filed: June 8, 2022
    Publication date: December 14, 2023
    Inventors: Hejie Li, Shai Birmaher, Michael A. Benjamin
  • Patent number: 11821366
    Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
    Type: Grant
    Filed: June 17, 2021
    Date of Patent: November 21, 2023
    Assignee: General Electric Company
    Inventors: Brandon W. Miller, Robert Jon McQuiston, Stefan Joseph Cafaro, Eric Richard Westervelt, Michael A. Benjamin, Joel M. Haynes, Hejie Li
  • Publication number: 20230366547
    Abstract: A hollow plank of a combustor liner defining a combustion chamber including an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of lateral walls coupled to the inner wall and the outer wall to define a cavity, and a partition wall connected to the plurality of lateral walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The one or more outer openings communicate with the first sub-cavity and communicate through a plurality of tubes with the second sub-cavity. The plurality of inner openings communicate with the second sub-cavity and communicate with the first sub-cavity through one or more bypass tubes. The first sub-cavity or the second sub-cavity, or both, are frequency tuned to reduce combustion dynamic frequencies.
    Type: Application
    Filed: September 15, 2022
    Publication date: November 16, 2023
    Inventors: Hiranya Nath, Ravindra Shankar Ganiger, Michael A. Benjamin
  • Publication number: 20230366550
    Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.
    Type: Application
    Filed: July 20, 2023
    Publication date: November 16, 2023
    Inventors: Perumallu Vukanti, Varun S. Lakshmanan, Michael T. Bucaro, Pradeep Naik, Steven C. Vise, Michael A. Benjamin
  • 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: 20230358170
    Abstract: A diffuser for a combustor of a turbomachine engine. The diffuser includes a body having a first annular surface and a second annular surface that define a passage, the passage being configured to cause air to flow along the passage to a first component of the combustor. The first annular surface includes an opening that is configured to cause air to flow in a direction away from the passage to a second component of the combustor.
    Type: Application
    Filed: May 9, 2022
    Publication date: November 9, 2023
    Inventors: Juntao Zhang, Nicholas R. Overman, Steven C. Vise, Andrew Wickersham, Michael A. Benjamin
  • Patent number: 11795879
    Abstract: A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.
    Type: Grant
    Filed: January 31, 2022
    Date of Patent: October 24, 2023
    Assignee: General Electric Company
    Inventors: Krishnakumar Venkatesan, Michael A. Benjamin, Michael T. Bucaro
  • Publication number: 20230332549
    Abstract: A fuel temperature control system and a method of controlling a fuel temperature for a turbine engine including supplying an aviation fuel to a fuel nozzle fluidly coupled to a combustion chamber. A fuel temperature sensor for determining at least one input parameter to define an inlet fuel temperature of the aviation fuel in the fuel nozzle. A controller for receiving the at least one input parameter and for calculating a calculated flow number in the fuel nozzle. The controller capable of comparing the calculated flow number and a reference flow number associated with a threshold during a steady state condition to determine if the aviation fuel is boiling inside the fuel nozzle.
    Type: Application
    Filed: April 13, 2022
    Publication date: October 19, 2023
    Inventors: Hejie Li, Michael A. Benjamin, Nicholas Ryan Overman
  • Patent number: 11788724
    Abstract: A combustor liner has an outer liner and an inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The outer liner and the inner liner each have a converging-diverging section extending into the dilution zone of the combustion chamber and form a throat between them. A bridge member extends across the converging-diverging sections to form a damper cavity therebetween. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat, and includes a damper inlet feed member on a downstream portion of the converging-diverging section, so that an acoustic damper is defined by the converting-diverging section, the bridge, and the damper inlet feed. The acoustic damper dampens acoustic characteristics of the combustor.
    Type: Grant
    Filed: September 2, 2022
    Date of Patent: October 17, 2023
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Hiranya Nath, Ravindra Shankar Ganiger, Michael A. Benjamin
  • Patent number: 11774100
    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 combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
    Type: Grant
    Filed: April 21, 2022
    Date of Patent: October 3, 2023
    Assignee: General Electric Company
    Inventors: Nayan Vinod Patel, Michael A. Benjamin
  • 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: 20230303940
    Abstract: A component and a system for mitigating coke formation during delivery of a hydrocarbon fluid. The component includes a contact surface configured to be in contact with the hydrocarbon fluid. Tuning the zeta potential of the contact surface allows selective attraction and/or repulsion of coke-catalyzing materials, metal ions, heteroatomic hydrocarbons, and/or coke precursors present in the hydrocarbon fluid. A method of mitigating coke formation during delivery of a hydrocarbon fluid includes tuning a zeta potential of the contact surface of the component and injecting or circulating the hydrocarbon fluid through the system such that the contact surface selectively attracts and/or repels coke-catalyzing materials, metal ions, heteroatomic hydrocarbons, and/or coke precursors present in the hydrocarbon fluid.
    Type: Application
    Filed: July 28, 2022
    Publication date: September 28, 2023
    Inventors: Arundhati Sengupta, Karthick Gourishankar, Narayanan Janakiraman, Lawrence B. Kool, Sanjay Kumar Sondhi, Michael A. Benjamin, Hejie Li
  • 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