Patents by Inventor Timothy P. Gabb

Timothy P. Gabb 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).

  • Low density, high creep resistant single crystal superalloy for turbine airfoils
    Patent number: 7261783
    Abstract: A nickel-base superalloy article for use in turbines has increased creep resistance and lower density. The superalloy article includes, as measured in % by weight, 6.0-12.0% Mo, 5.5-6.5% Al, 3.0-7.0% Ta, 0-15% Co, 2.0-6.0% Cr, 1.0-4.0% Re, 0-1.5% W, 0-1.5% Ru, 0-2.0%-Ti, 0-3.0% Nb, 0-0.2% Hf, 0-0.02% Y, 0.001-0.005% B, 0.01-0.04% C, and a remainder including nickel plus impurities.
    Type: Grant
    Filed: September 22, 2004
    Date of Patent: August 28, 2007
    Assignee: The United States of America as Represented by the Administrator of NASA
    Inventors: Rebecca A. MacKay, Timothy P. Gabb, James L Smialek, Michael V. Nathal
  • Nickel base superalloy turbine disk
    Patent number: 6974508
    Abstract: A low solvus, high refractory alloy having unusually versatile processing mechanical property capabilities for advanced disks and rotors in gas turbine engines. The nickel base superalloy has a composition consisting essentially of, in weight percent, 3.0–4.0 Al, 0.02–0.04 B, 0.02–0.05 C, 12.0–14.0 Cr, 19.0–22.0 Co, 2.0–3.5 Mo, greater than 1.0 to 2.1 Nb, 1.3 to 2.1 Ta, 3.0–4.0 Ti, 4.1 to 5.0 W, 0.03–0.06 Zr, and balance essentially Ni aid incidental impurities. The superalloy combines ease of processing with high temperature capabilities to be suitable for use in various turbine engine disk, impeller, and shaft applications. The Co and Cr levels of the superalloy can provide low solvus temperature for high processing versatility. The W, Mo, Ta, and Nb refractory element levels of the superalloy can provide sustained strength, creep, and dwell crack growth resistance at high temperatures.
    Type: Grant
    Filed: October 29, 2002
    Date of Patent: December 13, 2005
    Assignee: The United States of America as represented by the United States National Aeronautics and Space Administration
    Inventors: Timothy P. Gabb, John Gayda, Ignacy Telesman, Pete T. Kantzos
  • Heat treatment devices and method of operation thereof to produce dual microstructure superalloy disks
    Patent number: 6660110
    Abstract: A heat treatment assembly and heat treatment methods are disclosed for producing different microstructures in the bore and rim portions of nickel-based superalloy disks, particularly suited for gas turbine applications. The heat treatment assembly is capable of being removed from the furnace and disassembled to allow rapid fan or oil quenching of the disk. For solutioning heat treatments of the disk, temperatures higher than that of this solvus temperature of the disk are used to produce coarse grains in the rim of each disk so as to give maximum creep and dwell crack resistance at the rim service temperature. At the same time, solution temperature lower than the solvus temperature of the disk are provided to produce fine grain in the bore of the disk so as to give maximum strength and low cycle fatigue resistance.
    Type: Grant
    Filed: April 8, 2002
    Date of Patent: December 9, 2003
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: John Gayda, Timothy P. Gabb, Peter T. Kantzos