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).

  • Publication number: 20240401809
    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: August 15, 2024
    Publication date: December 5, 2024
    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: 20240401807
    Abstract: A turbine engine includes a combustor having a main combustion chamber, an annular dome positioned at a first angle ? with respect to a longitudinal centerline axis of the combustor, and a secondary combustion chamber. The secondary combustion chamber is defined by a portion of the annular dome and an aft wall positioned at a second angle ? with respect to the longitudinal centerline axis. A pilot mixer is disposed through the annular dome and injects a pilot mixer fuel-air mixture at a pilot mixer fuel-air mixture angle into the main combustion chamber and generates a first recirculation zone. A main mixer is disposed through the aft wall or the annular dome at the secondary combustion chamber. The main mixer injects a main mixer fuel-air mixture at a main mixer fuel-air mixture angle into the secondary combustion chamber to produce combustion gases and generates a second recirculation zone.
    Type: Application
    Filed: May 31, 2023
    Publication date: December 5, 2024
    Inventors: Hiranya Nath, Michael A. Benjamin, Richard W. Stickles, Clayton S. Cooper, Steven C. Vise, Ranganatha Narasimha Chiranthan
  • Patent number: 12152780
    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: Grant
    Filed: April 18, 2023
    Date of Patent: November 26, 2024
    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: 12152779
    Abstract: A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.
    Type: Grant
    Filed: August 22, 2023
    Date of Patent: November 26, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Pradeep Naik, Clayton S. Cooper, Perumallu Vukanti, Michael A. Benjamin, Steven C. Vise, Sripathi Mohan
  • Publication number: 20240359816
    Abstract: A hydrogen fuel including a safety marker and a method and apparatus for adding the safety marker to the hydrogen fuel. The hydrogen fuel may be stored in a tank in a liquid phase and then heated to at least one of a gaseous phase and a supercritical phase. The safety marker may be added to the hydrogen fuel when the hydrogen fuel is in the at least one of the gaseous phase and the supercritical phase after heating the hydrogen fuel. The hydrogen fuel may be delivered in the at least one of the gaseous phase and the supercritical phase to a power generator, such as a gas turbine engine. The safety marker may be a visual safety marker, such as a noble gas, or an odorant.
    Type: Application
    Filed: July 10, 2024
    Publication date: October 31, 2024
    Inventors: Arthur W. Sibbach, Michael A. Benjamin, Paul Burchell Glaser
  • Patent number: 12130016
    Abstract: A combustor for a turbine engine includes a main combustion chamber, an annular dome, and a secondary combustion chamber positioned downstream of the annular dome. A plurality of first mixing assemblies are disposed through the annular dome and include a pilot mixer. The pilot mixer injects a pilot mixer fuel-air mixture axially into the main combustion chamber and generates a first recirculation zone within the main combustion chamber. A plurality of second mixing assemblies are disposed at the secondary combustion chamber axially aft of the first mixing assemblies and include a main mixer. The main mixer injects a main mixer fuel-air mixture into the secondary combustion chamber to produce combustion gases and to generate a second recirculation zone within the secondary combustion chamber axially aft of the first recirculation zone. The secondary combustion chamber injects the combustion gases into the main combustion chamber.
    Type: Grant
    Filed: May 31, 2023
    Date of Patent: October 29, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Hiranya Nath, Clayton S. Cooper, Steven C. Vise, Michael A. Benjamin, Pradeep Naik, Ranganatha Narasimha Chiranthan, Perumallu Vukanti, Sibtosh Pal
  • Patent number: 12130013
    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: Grant
    Filed: August 6, 2021
    Date of Patent: October 29, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Steven C. Vise, Clayton S. Cooper, Michael A. Benjamin, Pradeep Naik, Kwanwoo Kim, Shai Birmaher, Perumallu Vukanti, Saket Singh, Karthikeyan Sampath
  • Patent number: 12116935
    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: May 1, 2023
    Date of Patent: October 15, 2024
    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: 20240328622
    Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
    Type: Application
    Filed: June 7, 2024
    Publication date: October 3, 2024
    Inventors: Michael A. Benjamin, Manampathy G. Giridharan
  • Publication number: 20240328360
    Abstract: A turbine engine and method of operation with a combustor as shown and described. The turbine engine including a combustor comprising an annular array of rich cups and an annular array of lean cups. A method for controlling nitrogen oxides including injecting a fuel/air mixture from the lean cups and the rich cups.
    Type: Application
    Filed: June 13, 2024
    Publication date: October 3, 2024
    Inventors: Michael T. Bucaro, Manampathy G. Giridharan, Pradeep Naik, Sripathi Mohan, Michael A. Benjamin, Steven C. Vise, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan
  • Patent number: 12104795
    Abstract: A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.
    Type: Grant
    Filed: May 25, 2022
    Date of Patent: October 1, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Ravindra Shankar Ganiger, Hiranya Nath, Michael A. Benjamin
  • Publication number: 20240318598
    Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
    Type: Application
    Filed: June 7, 2024
    Publication date: September 26, 2024
    Inventors: Michael A. Benjamin, Manampathy G. Giridharan
  • Publication number: 20240318597
    Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
    Type: Application
    Filed: June 7, 2024
    Publication date: September 26, 2024
    Inventors: Michael A. Benjamin, Manampathy G. Giridharan
  • Publication number: 20240318821
    Abstract: A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and at least one dilution passage. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The at least one dilution passage extending through at least one of the inner liner or the outer liner. The at least one dilution passage extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.
    Type: Application
    Filed: March 20, 2023
    Publication date: September 26, 2024
    Inventors: Manampathy G. Giridharan, Pradeep Naik, Michael A. Benjamin
  • Publication number: 20240309804
    Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
    Type: Application
    Filed: May 24, 2024
    Publication date: September 19, 2024
    Inventors: Michael A. Benjamin, Manampathy G. Giridharan
  • Publication number: 20240309805
    Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
    Type: Application
    Filed: May 24, 2024
    Publication date: September 19, 2024
    Inventors: Michael A. Benjamin, Manampathy G. Giridharan
  • Publication number: 20240310048
    Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
    Type: Application
    Filed: May 24, 2024
    Publication date: September 19, 2024
    Inventors: Michael A. Benjamin, Manampathy G. Giridharan
  • Patent number: 12092332
    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: Grant
    Filed: February 18, 2022
    Date of Patent: September 17, 2024
    Assignee: General Electric Company
    Inventors: Pradeep Naik, Ajoy Patra, Michael T. Bucaro, Perumallu Vukanti, Steven C. Vise, Michael A. Benjamin, Manampathy G. Giridharan, Saket Singh, Clayton S. Cooper
  • Patent number: 12085281
    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: July 11, 2023
    Date of Patent: September 10, 2024
    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: 20240295323
    Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
    Type: Application
    Filed: May 10, 2024
    Publication date: September 5, 2024
    Inventors: Michael A. Benjamin, Manampathy G. Giridharan