Patents by Inventor Gregory C. Carlucci

Gregory C. Carlucci 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