Patents by Inventor Kalman V. Wagner

Kalman V. Wagner 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).

  • Contoured endwall for a gas turbine engine
    Patent number: 10920599
    Abstract: A vane for a gas turbine engine according to an example of the present disclosure includes, among other things, first and second endwalls each having a radially facing surface that bounds a gas path, an airfoil section extending in a radial direction between the first and second endwalls, extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and extending in a circumferential direction between pressure and suction sides. The radially facing surface of each of the first and second endwalls is axially sloped such that the gas path converges in the axial direction between the airfoil leading and trailing edges. The first endwall has an axisymmetric contour at least partially swept in the circumferential direction from each of the pressure and suction sides.
    Type: Grant
    Filed: January 31, 2019
    Date of Patent: February 16, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Abhir A. Adhate, Frank M. Prior, Kalman V. Wagner
  • CONTOURED ENDWALL FOR A GAS TURBINE ENGINE
    Publication number: 20200248572
    Abstract: A vane for a gas turbine engine according to an example of the present disclosure includes, among other things, first and second endwalls each having a radially facing surface that bounds a gas path, an airfoil section extending in a radial direction between the first and second endwalls, extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and extending in a circumferential direction between pressure and suction sides. The radially facing surface of each of the first and second endwalls is axially sloped such that the gas path converges in the axial direction between the airfoil leading and trailing edges. The first endwall has an axisymmetric contour at least partially swept in the circumferential direction from each of the pressure and suction sides.
    Type: Application
    Filed: January 31, 2019
    Publication date: August 6, 2020
    Inventors: Abhir A. Adhate, Frank M. Prior, Kalman V. Wagner