Patents by Inventor Harry Holloman

Harry Holloman 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).

  • Turbine airfoil with trailing edge features and casting core
    Patent number: 11415000
    Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.
    Type: Grant
    Filed: June 4, 2018
    Date of Patent: August 16, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Ching-Pang Lee, Jae Y. Um, Sin Chien Siw, Anthony Waywood, Harry Holloman, Steven Koester
  • Turbine rotor airfoil and corresponding method for reducing pressure loss in a cavity within a blade
    Patent number: 11111795
    Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.
    Type: Grant
    Filed: August 7, 2018
    Date of Patent: September 7, 2021
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Ching-Pang Lee, Harry Holloman, Steven Koester, Jae Y. Um, Sin Chien Siw
  • TURBINE AIRFOIL WITH TRAILING EDGE FEATURES AND CASTING CORE
    Publication number: 20210140321
    Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.
    Type: Application
    Filed: June 4, 2018
    Publication date: May 13, 2021
    Inventors: Ching-Pang Lee, Jae Y. Um, Sin Chien Siw, Anthony Waywood, Harry Holloman, Steven Koester
  • TURBINE ROTOR AIRFOIL AND CORRESPONDING METHOD FOR REDUCING PRESSURE LOSS IN A CAVITY WITHIN A BLADE
    Publication number: 20210025278
    Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.
    Type: Application
    Filed: August 7, 2018
    Publication date: January 28, 2021
    Inventors: Ching-Pang Lee, Harry Holloman, Steven Koester, Jae Y. Um, Sin Chien Siw
  • Integrated circuit cooled turbine blade
    Patent number: 9745853
    Abstract: A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.
    Type: Grant
    Filed: August 31, 2015
    Date of Patent: August 29, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Ching-Pang Lee, Nan Jiang, Jae Y. Um, Harry Holloman, Steven Koester
  • INTEGRATED CIRCUIT COOLED TURBINE BLADE
    Publication number: 20170058678
    Abstract: A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.
    Type: Application
    Filed: August 31, 2015
    Publication date: March 2, 2017
    Inventors: Ching-Pang Lee, Nan Jiang, Jae Y. Um, Harry Holloman, Steven Koester