Patents by Inventor Roger Peckham

Roger Peckham 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).

  • System and method for turbine blade clearance control
    Patent number: 10184348
    Abstract: A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is minimized upon determining that both the aircraft gas turbine engine is generating a substantially constant thrust and the fuel-saving mode is enabled. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is then selectively increased to a predetermined clearance, and a change in aircraft gas turbine engine thrust is prevented until the predetermined clearance is achieved.
    Type: Grant
    Filed: December 5, 2013
    Date of Patent: January 22, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Gregory C. Carlucci, Glenn Alexander Knight, Jim Rumbo, Dennis D Loots, Roger Peckham, Marko Bacic, James Kenneth Haberstock
  • SYSTEM AND METHOD FOR TURBINE BLADE CLEARANCE CONTROL
    Publication number: 20150159500
    Abstract: A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is minimized upon determining that both the aircraft gas turbine engine is generating a substantially constant thrust and the fuel-saving mode is enabled. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is then selectively increased to a predetermined clearance, and a change in aircraft gas turbine engine thrust is prevented until the predetermined clearance is achieved.
    Type: Application
    Filed: December 5, 2013
    Publication date: June 11, 2015
    Inventors: Gregory C. Carlucci, Glenn Alexander Knight, Jim Rumbo, Dennis D. Loots, Roger Peckham, Marko Bacic, James Kenneth Haberstock
  • FLIGHT MANAGEMENT COMPUTER LATERAL ROUTE RECAPTURE
    Publication number: 20060025899
    Abstract: An aircraft flight management system having a flight management computer that stores a pre-planned lateral route of flight of the aircraft comprising a plurality of successive waypoints to be overflown, the next proximate waypoint being an active waypoint, a method providing a return-to-path maneuver in the event that the aircraft deviates from the pre-planned route, including selecting a new active waypoint, calculating a return-to-path route to overfly the new active waypoint, and selectably accepting the calculated return-to-path route.
    Type: Application
    Filed: July 25, 2003
    Publication date: February 2, 2006
    Inventors: Roger Peckham, Jimmy Rumbo