Patents by Inventor Brian V. Winebrenner

Brian V. Winebrenner 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).

  • FINAL TAKEOFF SPEED DETERMINATION FOR AN AIRCRAFT
    Publication number: 20230166857
    Abstract: A system of an aircraft includes one or more gas turbine engines and a controller. The controller is configured to detect a pre-takeoff condition of the aircraft and determine one or more control parameters for one or more current conditions at a target location of the aircraft. The controller is further configured to determine a final takeoff speed of the one or more gas turbine engines based on the one or more control parameters. At least one of the one or more gas turbine engines is controlled to accelerate to the final takeoff speed after transitioning from the pre-takeoff condition to a takeoff condition.
    Type: Application
    Filed: November 29, 2022
    Publication date: June 1, 2023
    Inventors: David Wasselin, Nancy Poisson, Brian V. Winebrenner, Bradley C. Schafer, Ramesh Rajagopalan
  • Real time model based compressor control
    Patent number: 9540944
    Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to generate a real-time estimate of compressor stall margin from an engine model, and command engine actuators to correct for the difference between the real time estimate of compressor stall margin and a required stall margin.
    Type: Grant
    Filed: September 28, 2012
    Date of Patent: January 10, 2017
    Assignee: United Technologies Corporation
    Inventors: Richard P. Meisner, Brian V. Winebrenner, Matthew R. Feulner, Boris Karpman, Juan A. Marcos, David L. Ma
  • REAL TIME MODEL BASED COMPRESSOR CONTROL
    Publication number: 20140093350
    Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to generate a real-time estimate of compressor stall margin from an engine model, and command engine actuators to correct for the difference between the real time estimate of compressor stall margin and a required stall margin.
    Type: Application
    Filed: September 28, 2012
    Publication date: April 3, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Richard P. Meisner, Brian V. Winebrenner, Matthew R. Feulner, Boris Karpman, Juan A. Marcos, David L. Ma