Patents by Inventor R. Glenn Swaffar

R. Glenn Swaffar 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 transition liner assembly and repair
    Patent number: 7185432
    Abstract: A method of repairing a damaged combustion gas transition liner for a gas turbine engine and an improved damage-resistant transition liner that mounts adjacent to the edge of one of the engine's combustion chambers. In a particular embodiment, the gas turbine engine is a reverse flow type and the transition liner has a scalloped, circular shape with a damaged outer edge portion. The outer edge portion of the liner is removed and replaced with a new ring-shaped edge portion. The new ring-shaped edge portion has a layer of damage-resistant material that is more robust than the original liner material. The layer of damage-resistant material is located such that it will be adjacent to the edge of the combustion chamber when the gas turbine engine is reassembled. A new transition liner assembly with the damage-resistant edge also is provided.
    Type: Grant
    Filed: February 28, 2005
    Date of Patent: March 6, 2007
    Assignee: Honeywell International, Inc.
    Inventor: R. Glenn Swaffar
  • Gas turbine engine transition liner assembly and repair
    Patent number: 6925810
    Abstract: A method of repairing a damaged combustion gas transition liner for a gas turbine engine and an improved damage-resistant transition liner that mounts adjacent to the edge of one of the engine's combustion chambers. In a particular embodiment, the gas turbine engine is a reverse flow type and the transition liner has a scalloped, circular shape with a damaged outer edge portion. The outer edge portion of the liner is removed and replaced with a new ring-shaped edge portion. The new ring-shaped edge portion has a layer of damage-resistant material that is more robust than the original liner material. The layer of damage-resistant material is located such that it will be adjacent to the edge of the combustion chamber when the gas turbine engine is reassembled. A new transition liner assembly with the damage-resistant edge also is provided.
    Type: Grant
    Filed: November 8, 2002
    Date of Patent: August 9, 2005
    Assignee: Honeywell International, Inc.
    Inventor: R. Glenn Swaffar
  • Gas turbine engine transition liner assembly and repair
    Publication number: 20040088988
    Abstract: A method of repairing a damaged combustion gas transition liner for a gas turbine engine and an improved damage-resistant transition liner that mounts adjacent to the edge of one of the engine's combustion chambers. In a particular embodiment, the gas turbine engine is a reverse flow type and the transition liner has a scalloped, circular shape with a damaged outer edge portion. The outer edge portion of the liner is removed and replaced with a new ring-shaped edge portion. The new ring-shaped edge portion has a layer of damage-resistant material that is more robust than the original liner material. The layer of damage-resistant material is located such that it will be adjacent to the edge of the combustion chamber when the gas turbine engine is reassembled. A new transition liner assembly with the damage-resistant edge also is provided.
    Type: Application
    Filed: November 8, 2002
    Publication date: May 13, 2004
    Inventor: R. Glenn Swaffar