Patents by Inventor David Fasig

David Fasig 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).

  • Clearance control assembly
    Patent number: 11970946
    Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.
    Type: Grant
    Filed: July 29, 2021
    Date of Patent: April 30, 2024
    Assignee: General Electric Company
    Inventors: Travis J. Packer, James Hamilton Grooms, David Fasig, Richard William Jendrix, Scott Alan Schimmels, Bradford Alan Tracey, Michael Alan Hile, Thomas Ryan Wallace
  • CLEARANCE CONTROL ASSEMBLY
    Publication number: 20230035302
    Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.
    Type: Application
    Filed: July 29, 2021
    Publication date: February 2, 2023
    Inventors: Travis J. Packer, James Hamilton Grooms, David Fasig, Richard William Jendrix, Scott Alan Schimmels, Bradford Alan Tracey, Michael Alan Hile, Thomas Ryan Wallace
  • Combustion System Deflection Mitigation Structure
    Publication number: 20190368381
    Abstract: A turbine engine including a first outer casing and a second outer casing coupled together at a flange. The first outer casing and the second outer casing are together disposed around a core engine. An inner casing assembly is extended from the flange between the first outer casing and the second outer casing. A flow circuit is defined between the first outer casing, the inner casing assembly, and the second outer casing.
    Type: Application
    Filed: May 30, 2018
    Publication date: December 5, 2019
    Inventors: Anthony Paul Greenwood, Brian Michael Dixon, Nestor Martinez Toro, David Fasig, Kimbra Chaplin, Ashish Narayan, Jeremy Kevin Payne