Patents by Inventor Thomas Schlesinger

Thomas Schlesinger 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).

  • Gas turbine or compressor blade
    Patent number: 7458779
    Abstract: A gas turbine or compressor blade, includes a convex outer surface or suction side and a concave inner surface or pressure side, these sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases and terminating on a platform, one part of which includes a downstream fairing that includes at least one through-notch that extends substantially between a transverse line passing through the trailing edge and the downstream end of the fairing.
    Type: Grant
    Filed: August 18, 2005
    Date of Patent: December 2, 2008
    Assignee: SNECMA
    Inventors: Eric Stephen Bil, Nicolas Hervy, Thomas Schlesinger
  • Rotor blade for a compressor or a gas turbine
    Patent number: 7399163
    Abstract: Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.
    Type: Grant
    Filed: August 18, 2005
    Date of Patent: July 15, 2008
    Assignee: SNECMA
    Inventors: Eric Stephan Bil, Chantal Gisele Giot, Thomas Schlesinger
  • Rotor blade for a compressor or a gas turbine
    Publication number: 20070292271
    Abstract: Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, comprising a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.
    Type: Application
    Filed: August 18, 2005
    Publication date: December 20, 2007
    Applicant: SNECMA
    Inventors: Eric Bil, Chantal Giot, Thomas Schlesinger
  • Gas turbine or compressor blade
    Publication number: 20070243067
    Abstract: Gas turbine or compressor blade, comprising a convex outer surface or suction side and a concave inner surface or pressure side, these sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases and terminating on a platform, one part of which includes a downstream fairing that includes at least one through-notch that extends substantially between a transverse line passing through the trailing edge and the downstream end of the fairing.
    Type: Application
    Filed: August 18, 2005
    Publication date: October 18, 2007
    Applicant: SNECMA
    Inventors: Eric Bil, Nicolas Hervy, Thomas Schlesinger