Patents by Inventor Egon Salimusaj

Egon Salimusaj 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).

  • Component with feather seal slots for a gas turbine engine
    Patent number: 11840930
    Abstract: A vane for a gas turbine engine, the vane including: an inner diameter platform and an outer diameter platform and an airfoil that extends between the inner diameter platform and the outer diameter platform, the airfoil having a leading edge, a trailing edge, a pressure side and a suction side, the inner diameter platform has a suction side mate face and a pressure side mate face, wherein the suction side mate face and the pressure side mate face of the inner diameter platform have an axial feather seal slot and a radial seal slot, the axial feather seal slot includes a leading edge portion that extends from the radial seal slot towards a leading edge of the inner diameter platform and a trailing edge portion that extends from the radial seal slot towards a trailing edge of the inner diameter platform, and a chamfer extends between the radial seal slot and the trailing edge portion of the axial feather seal slot.
    Type: Grant
    Filed: May 17, 2019
    Date of Patent: December 12, 2023
    Assignee: RTX CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Craig R. McGarrah, Kyle J. Brevick, Egon Salimusaj
  • Seal for a gas turbine engine
    Patent number: 11111802
    Abstract: A component for a gas turbine engine includes a first platform that has a first pair of circumferential surfaces and a first axially aft surface. A first axially extending seal slot is located in each of the first pair of circumferential surfaces and the first axially aft surface. A first cover plate is attached to the first axially aft surface and encloses at least a portion of the first axially extending seal slots.
    Type: Grant
    Filed: May 1, 2019
    Date of Patent: September 7, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Egon Salimusaj
  • COMPONENT WITH FEATHER SEAL SLOTS FOR A GAS TURBINE ENGINE
    Publication number: 20200362715
    Abstract: A vane for a gas turbine engine, the vane including: an inner diameter platform and an outer diameter platform and an airfoil that extends between the inner diameter platform and the outer diameter platform, the airfoil having a leading edge, a trailing edge, a pressure side and a suction side, the inner diameter platform has a suction side mate face and a pressure side mate face, wherein the suction side mate face and the pressure side mate face of the inner diameter platform have an axial feather seal slot and a radial seal slot, the axial feather seal slot includes a leading edge portion that extends from the radial seal slot towards a leading edge of the inner diameter platform and a trailing edge portion that extends from the radial seal slot towards a trailing edge of the inner diameter platform, and a chamfer extends between the radial seal slot and the trailing edge portion of the axial feather seal slot.
    Type: Application
    Filed: May 17, 2019
    Publication date: November 19, 2020
    Inventors: Tracy A. Propheter-Hinckley, Craig R. McGarrah, Kyle J. Brevick, Egon Salimusaj
  • SEAL FOR A GAS TURBINE ENGINE
    Publication number: 20200347738
    Abstract: A component for a gas turbine engine includes a first platform that has a first pair of circumferential surfaces and a first axially aft surface. A first axially extending seal slot is located in each of the first pair of circumferential surfaces and the first axially aft surface. A first cover plate is attached to the first axially aft surface and encloses at least a portion of the first axially extending seal slots.
    Type: Application
    Filed: May 1, 2019
    Publication date: November 5, 2020
    Inventors: Tracy A. Propheter-Hinckley, Egon Salimusaj