Patents by Inventor Brian Edward Krupp

Brian Edward Krupp 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).

  • Compensating for blade tip clearance deterioration in active clearance control
    Patent number: 7431557
    Abstract: A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.
    Type: Grant
    Filed: May 25, 2006
    Date of Patent: October 7, 2008
    Assignee: General Electric Company
    Inventors: William Lee Herron, Matthew William Wiseman, Jon Michael Vishnauski, Brian Edward Krupp, Ronald George Maruscik
  • Compensating for blade tip clearance deterioration in active clearance control
    Publication number: 20070276578
    Abstract: A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.
    Type: Application
    Filed: May 25, 2006
    Publication date: November 29, 2007
    Inventors: William Lee Herron, Matthew William Wiseman, Jon Micheal Vishnauski, Brian Edward Krupp, Ronald George Maruscik