Patents by Inventor Vincent E. Simms

Vincent E. Simms 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).

  • Turbine vane cooling arrangement
    Patent number: 10648363
    Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
    Type: Grant
    Filed: December 28, 2017
    Date of Patent: May 12, 2020
    Assignee: United Technologies Corporation
    Inventors: Shawn M. McMahon, Christopher Whitfield, Nicholas M. LoRicco, Steven Bruce Gautschi, Vincent E. Simms, Justin M. Aniello, Thomas Allwood, Richard M. Salzillo, Jeffery Scott Hembree, Sr.
  • Doublet vane assembly for a gas turbine engine
    Patent number: 10533425
    Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.
    Type: Grant
    Filed: December 28, 2017
    Date of Patent: January 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Shawn M. McMahon, Christopher Whitfield, Nicholas M. LoRicco, Steven Bruce Gautschi, Vincent E. Simms, Justin M. Aniello, Thomas Allwood, Richard M. Salzillo, Jeffery Scott Hembree, Sr.
  • TURBINE VANE COOLING ARRANGEMENT
    Publication number: 20190203612
    Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
    Type: Application
    Filed: December 28, 2017
    Publication date: July 4, 2019
    Inventors: Shawn M. McMahon, Christopher Whitfield, Nicholas M. LoRicco, Steven Bruce Gautschi, Vincent E. Simms, Justin M. Aniello, Thomas Allwood, Richard M. Salzillo, Jeffery Scott Hembree, SR.
  • DOUBLET VANE ASSEMBLY FOR A GAS TURBINE ENGINE
    Publication number: 20190203602
    Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.
    Type: Application
    Filed: December 28, 2017
    Publication date: July 4, 2019
    Inventors: Shawn M. McMahon, Christopher Whitfield, Nicholas M. LoRicco, Steven Bruce Gautschi, Vincent E. Simms, Justin M. Aniello, Thomas Allwood, Richard M. Salzillo, Jeffery Scott Hembree, SR.
  • Chordal seal
    Patent number: 9863259
    Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: January 9, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark A. Boeke, Kevin Rajchel, Mosheshe Camara-khary Blake, Vincent E. Simms
  • CHORDAL SEAL
    Publication number: 20160333712
    Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.
    Type: Application
    Filed: May 11, 2015
    Publication date: November 17, 2016
    Inventors: Mark A. Boeke, Kevin Rajchel, Mosheshe Camara-khary Blake, Vincent E. Simms