Patents by Inventor Andrew David Kemp

Andrew David Kemp 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).

  • Accelerator insert for a gas turbine engine airfoil
    Patent number: 10443407
    Abstract: An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.
    Type: Grant
    Filed: February 15, 2016
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: Robert David Briggs, Shawn Michael Pearson, Andrew David Kemp, Gulcharan Singh Brainch
  • Method and system for sealing an annulus
    Patent number: 9896970
    Abstract: A method and system for a compartment baffle system are provided. The compartment baffle system includes a first baffle portion extending along an axial length of a casing, the first baffle portion extending radially outwardly from an outer surface of the casing and a second baffle portion extending at least partially radially outwardly from the first baffle portion. The second baffle portion further includes a radially inner edge supported by the first baffle portion and a radially outer edge extending proximate an inner surface of a radially outer cowl. The compartment baffle system also includes a gap extending between the radially outer edge and the inner surface.
    Type: Grant
    Filed: October 30, 2015
    Date of Patent: February 20, 2018
    Assignee: General Electric Company
    Inventors: Kyle Andrew Grose, Arjan Johannes Hegeman, Andrew David Kemp, John Michael Pyles
  • ACCELERATOR INSERT FOR A GAS TURBINE ENGINE AIRFOIL
    Publication number: 20170234145
    Abstract: An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.
    Type: Application
    Filed: February 15, 2016
    Publication date: August 17, 2017
    Inventors: Robert David Briggs, Shawn Michael Pearson, Andrew David Kemp, Gulcharan Singh Brainch
  • METHOD AND SYSTEM FOR SEALING AN ANNULUS
    Publication number: 20160201565
    Abstract: A method and system for a compartment baffle system are provided. The compartment baffle system includes a first baffle portion extending along an axial length of a casing, the first baffle portion extending radially outwardly from an outer surface of the casing and a second baffle portion extending at least partially radially outwardly from the first baffle portion. The second baffle portion further includes a radially inner edge supported by the first baffle portion and a radially outer edge extending proximate an inner surface of a radially outer cowl. The compartment baffle system also includes a gap extending between the radially outer edge and the inner surface.
    Type: Application
    Filed: October 30, 2015
    Publication date: July 14, 2016
    Inventors: Kyle Andrew GROSE, Arjan Johannes HEGEMAN, Andrew David KEMP, John Michael PYLES
  • Gas turbine engine bleed scoops
    Patent number: 6550254
    Abstract: A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.
    Type: Grant
    Filed: August 17, 2001
    Date of Patent: April 22, 2003
    Assignee: General Electric Company
    Inventors: Robert Proctor, Julius John Montgomery, Michael Jay Epstein, Roger Owen Barbe, Hai Buu Sam, James Bernar Ogzewalla, Andrew David Kemp, Bryan Keith Doloresco
  • Methods and systems for gas turbine engine bleed scoops
    Publication number: 20030033815
    Abstract: A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.
    Type: Application
    Filed: August 17, 2001
    Publication date: February 20, 2003
    Inventors: Robert Proctor, Julius John Montgomery, Michael Jay Epstein, Roger Owen Barbe, Hai Buu Sam, James Bernar Ogzewalla, Andrew David Kemp, Bryan Keith Doloresco