Patents by Inventor Don Tillman

Don Tillman 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).

  • Gas turbine engine turbine blade tip active clearance control system and method
    Patent number: 9266618
    Abstract: A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.
    Type: Grant
    Filed: November 18, 2013
    Date of Patent: February 23, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Don Tillman, Raymond Gage, Rich Barrett
  • GAS TURBINE ENGINE TURBINE BLADE TIP ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD
    Publication number: 20150142216
    Abstract: A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.
    Type: Application
    Filed: November 18, 2013
    Publication date: May 21, 2015
    Inventors: Don Tillman, Raymond Gage, Rich Barrett
  • COMBUSTION SECTIONS OF GAS TURBINE ENGINES WITH CONVECTION SHIELD ASSEMBLIES
    Publication number: 20130067932
    Abstract: A combustion section is provided for a gas turbine engine. The combustion section includes a first liner; a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein; a first case circumscribing the first liner and forming a first plenum with the first liner; and a convection shield assembly positioned between the first liner and the first case.
    Type: Application
    Filed: September 20, 2011
    Publication date: March 21, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Don Tillman