Patents by Inventor GLENN ALEXANDER KNIGHT

GLENN ALEXANDER KNIGHT 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
  • Control of a gas turbine engine
    Patent number: 9828869
    Abstract: A thrust demand signal is provided to a processor of a gas turbine engine and is modified, according to growth time constants of a rotor and/or a casing of the engine, in order to control the rotational speed or the rate of change of rotational speed of the engine so as to prevent contact between the rotor and the casing.
    Type: Grant
    Filed: November 10, 2014
    Date of Patent: November 28, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, Glenn Alexander Knight, Parag Vyas, Sean Patrick Ellis
  • CONTROL OF A GAS TURBINE ENGINE
    Publication number: 20150159499
    Abstract: A thrust demand signal is provided to a processor of a gas turbine engine and is modified, according to growth time constants of a rotor and/or a casing of the engine, in order to control the rotational speed or the rate of change of rotational speed of the engine so as to prevent contact between the rotor and the casing.
    Type: Application
    Filed: November 10, 2014
    Publication date: June 11, 2015
    Inventors: Marko BACIC, Glenn Alexander KNIGHT, Parag VYAS, Sean Patrick ELLIS
  • 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
  • GAS TURBINE ENGINE
    Publication number: 20100089019
    Abstract: A gas turbine engine having three shafts connecting respective high, intermediate and low-pressure turbines and compressors is characterised by an intermediate pressure turbine that includes two rotor stages.
    Type: Application
    Filed: May 20, 2009
    Publication date: April 15, 2010
    Applicant: ROLLS-ROYCE PLC
    Inventors: GLENN ALEXANDER KNIGHT, Martyn Richards, Mark David Taylor, Alan Robert Maguire