Patents by Inventor Brandon Lamar Bush

Brandon Lamar Bush 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).

  • COMPRESSOR ROTOR BLADE AIRFOILS
    Publication number: 20230250724
    Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
    Type: Application
    Filed: March 29, 2023
    Publication date: August 10, 2023
    Inventors: Marc Edward Blohm, Vasantharuban S, Michael James Dutka, Nandakumar A R, Sharan Shanti, Prakash Dalsania, Corey Lynn Hubbert, Siddaraja Mallikarjuna Devangada, Joshy John, Nancy Chaudhary, Abel Christena Francis, Brandon Lamar Bush, Jeremy Peter Latimer
  • COMPRESSOR ROTOR BLADE AIRFOILS
    Publication number: 20220372879
    Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.
    Type: Application
    Filed: August 17, 2021
    Publication date: November 24, 2022
    Inventors: Marc Edward Blohm, Vasantharuban S, Michael James Dutka, Nandakumar A R, Sharan Shanti, Prakash Dalsania, Corey Lynn Hubbert, Siddaraja Mallikarjuna Devangada, Joshy John, Nancy Chaudhary, Abel Christena Francis, Brandon Lamar Bush, Jeremy Peter Latimer
  • Compressor stator vane airfoils
    Patent number: 11293454
    Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, or Table VIII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: April 30, 2021
    Date of Patent: April 5, 2022
    Assignee: General Electric Company
    Inventors: Paul G. Deivernois, Marcus Edward Blohm, Michael James Dutka, Andrew Clifford Hart, Steven Lynn Huskins, Aaron David Williamson, Corey Lynn Hubbert, Venkata Siva Prasad Chaluvadi, Brandon Lamar Bush, Jeremy Peter Latimer
  • Combustor inlet flow conditioner
    Patent number: 10677466
    Abstract: A combustor includes an inlet flow conditioner. The inlet flow conditioner includes a sleeve that circumferentially surrounds a portion of a fuel nozzle assembly and that extends from a forward end of a combustion liner to an inner surface of an end cover. The sleeve defines a plurality of apertures circumferentially spaced about the sleeve. A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor. An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume.
    Type: Grant
    Filed: October 13, 2016
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Brandon Lamar Bush, Timothy James Purcell, Lucas John Stoia
  • COMBUSTOR INLET FLOW CONDITIONER
    Publication number: 20180106482
    Abstract: A combustor includes an inlet flow conditioner. The inlet flow conditioner includes a sleeve that circumferentially surrounds a portion of a fuel nozzle assembly and that extends from a forward end of a combustion liner to an inner surface of an end cover. The sleeve defines a plurality of apertures circumferentially spaced about the sleeve. A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor. An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume.
    Type: Application
    Filed: October 13, 2016
    Publication date: April 19, 2018
    Inventors: Jonathan Dwight Berry, Brandon Lamar Bush, Timothy James Purcell, Lucas John Stoia