Patents by Inventor John S. Tu, JR.

John S. Tu, JR. 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).

  • Co-swirl orientation of combustor effusion passages for gas turbine engine combustor
    Patent number: 10317080
    Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.
    Type: Grant
    Filed: December 3, 2014
    Date of Patent: June 11, 2019
    Assignee: United Technologies Corporation
    Inventors: John S. Tu, Jr., Timothy S. Snyder, James B. Hoke, James P. Bangerter, Dennis J. Duhamel, David A. Burns
  • CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    Publication number: 20160281988
    Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.
    Type: Application
    Filed: December 3, 2014
    Publication date: September 29, 2016
    Inventors: John S. Tu, JR., Timothy S. Snyder, James B. Hoke, James P. Bangerter, Dennis J. Duhamel, David A. Burns