Patents by Inventor Jeffrey Allen Kress

Jeffrey Allen Kress 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).

  • Methods and apparatus for operating gas turbine engines
    Patent number: 7607885
    Abstract: A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.
    Type: Grant
    Filed: July 31, 2006
    Date of Patent: October 27, 2009
    Assignee: General Electric Company
    Inventors: Blaine Charles Bosley, Sean Robert Keith, Jeffrey Allen Kress, Richard W. Albrecht, Jr.
  • METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES
    Publication number: 20090202337
    Abstract: A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.
    Type: Application
    Filed: July 31, 2006
    Publication date: August 13, 2009
    Inventors: Blaine Charles Bosley, Sean Robert Keith, Jeffrey Allen Kress, Richard W. Albrecht, JR.
  • Band cooled turbine nozzle
    Patent number: 6769865
    Abstract: A turbine nozzle includes hollow nozzle vanes mounted between outer and inner bands. The inner band includes an integral skirt around the perimeter thereof. A backing sheet of a honeycomb seal is mounted to the skirt to define a cavity therein. The inner band includes supply apertures for providing cooling air into the cavity, and the skirt includes forward and aft purge holes for discharging the cooling air therefrom. During operation, the air channeled through the cavity cools the backside of the inner band and is then discharged through the purge holes.
    Type: Grant
    Filed: March 22, 2002
    Date of Patent: August 3, 2004
    Assignee: General Electric Company
    Inventors: Jeffrey Allen Kress, Robert Alan Frederick
  • Band cooled turbine nozzle
    Publication number: 20030180141
    Abstract: A turbine nozzle includes hollow nozzle vanes mounted between outer and inner bands. The inner band includes an integral skirt around the perimeter thereof. A backing sheet of a honeycomb seal is mounted to the skirt to define a cavity therein. The inner band includes supply apertures for providing cooling air into the cavity, and the skirt includes forward and aft purge holes for discharging the cooling air therefrom. During operation, the air channeled through the cavity cools the backside of the inner band and is then discharged through the purge holes.
    Type: Application
    Filed: March 22, 2002
    Publication date: September 25, 2003
    Inventors: Jeffrey Allen Kress, Robert Alan Frederick