Skip to Content
Find More Like This
Return to Search

Rapid-quench axially staged combustor

United States Patent

5,996,351
December 7, 1999
View the Complete Patent at the US Patent & Trademark Office
A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber. In an alternative embodiment, the combustion chamber quench section further includes at least one middle region and at least a third plurality of quench holes disposed within the liner at the quench section having a third diameter to provide cooling jet penetration to at least one middle region of the quench section of the combustion chamber.
Feitelberg; Alan S. (Niskayuna, NY), Schmidt; Mark Christopher (Niskayuna, NY), Goebel; Steven George (Clifton Park, NY)
General Electric Company (Schenectady, NY)
08/ 888,252
July 7, 1997
This invention was made with Government support under Government Contract No. DEAC21-87-MC23170 awarded by the Department of Energy (DOE). The Government has certain rights to this invention.