Patents by Inventor Paul Edward Sabla

Paul Edward Sabla 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).

  • Patent number: 6546732
    Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for film cooling a portion of the deflector portion to facilitate reducing an operating temperature and extending a useful life of the combustor.
    Type: Grant
    Filed: April 27, 2001
    Date of Patent: April 15, 2003
    Assignee: General Electric Company
    Inventors: Craig Douglas Young, Paul Edward Sabla, Steven Clayton Vise
  • Patent number: 6530227
    Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for impingement cooling a portion of the flare cone portion to facilitate reducing an operating temperature and extending a useful life of the combustor.
    Type: Grant
    Filed: April 27, 2001
    Date of Patent: March 11, 2003
    Assignee: General Electric Co.
    Inventors: Craig Douglas Young, Paul Edward Sabla, Steven Clayton Vise
  • Patent number: 6389815
    Abstract: A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.
    Type: Grant
    Filed: September 8, 2000
    Date of Patent: May 21, 2002
    Assignee: General Electric Company
    Inventors: Harjit Singh Hura, Paul Edward Sabla, James Neil Cooper, Beverly Stephenson Duncan, Hukam Chand Mongia, Steven Joseph Lohmueller