Patents by Inventor Michael Loetzerich

Michael Loetzerich 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
    Patent number: 11519273
    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: Grant
    Filed: July 16, 2021
    Date of Patent: December 6, 2022
    Assignee: General Electric Company
    Inventors: Michael James Healy, Matthew John McKeever, Sabarinath Devarajan, Uday Krishna Pappala, Kevin Michael Barnett, Kumaran Vale Mudaliar, Wilfried Rick, Moorthi Subramaniyan, Karan Ghule, Denis Stankovic, Yu Wang, Marco Micheli, Mariadas Anton Charles Anandarajah, Michael Loetzerich
  • COMPRESSOR ROTOR BLADE AIRFOILS
    Publication number: 20220372878
    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: July 16, 2021
    Publication date: November 24, 2022
    Inventors: Michael James Healy, Matthew John McKeever, Sabarinath Devarajan, Uday Krishna Pappala, Kevin Michael Barnett, Kumaran Vale Mudaliar, Wilfried Rick, Moorthi Subramaniyan, Karan Ghule, Denis Stankovic, Yu Wang, Marco Micheli, Mariadas Anton Charles Anandarajah, Michael Loetzerich
  • Process for treating a coated gas turbine part, and coated gas turbine part
    Patent number: 6773753
    Abstract: The invention discloses a process for treating a ceramic protective layer (3) which is applied to the surface (2) of a gas turbine part (1). The roughness of the ceramic protective layer (3) is reduced at at least one first location (5), and the original roughness is retained at at least one second location (6). The roughness is advantageously retained at locations (6) on a turbine blade or vane (1) which are at risk of detachment, while the roughness of the remaining surface (2) is reduced in order to reduce the heat transfer to the surrounding hot-gas flow.
    Type: Grant
    Filed: August 5, 2002
    Date of Patent: August 10, 2004
    Assignee: Alstom Technology LTD
    Inventors: Gordon Anderson, Reinhard Fried, Michael Loetzerich, Markus Oehl, Stefan Schlechtriem, Joerg Stengele
  • Process for treating a coated gas turbine part, and coated gas turbine part
    Publication number: 20030035968
    Abstract: The invention discloses a process for treating a ceramic protective layer (3) which is applied to the surface (2) of a gas turbine part (1). The roughness of the ceramic protective layer (3) is reduced at at least one first location (5), and the original roughness is retained at at least one second location (6). The roughness is advantageously retained at locations (6) on a turbine blade or vane (1) which are at risk of detachment, while the roughness of the remaining surface (2) is reduced in order to reduce the heat transfer to the surrounding hot-gas flow.
    Type: Application
    Filed: August 5, 2002
    Publication date: February 20, 2003
    Inventors: Gordon Anderson, Reinhard Fried, Michael Loetzerich, Markus Oehl, Stefan Schlechtriem, Joerg Stengele