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Gas turbine engine combustor can with trapped vortex cavity

United States Patent

6,951,108
October 4, 2005
View the Complete Patent at the US Patent & Trademark Office
A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.
Burrus; David Louis (Cincinnati, OH), Joshi; Narendra Digamber (Cincinnati, OH), Haynes; Joel Meier (Niskayuna, NY), Feitelberg; Alan S. (Niskayuna, NY)
General Electric Company (Schenectady, NY)
10/ 762,993
January 22, 2004
This Invention was made with Government support under Contract No. DE-FC26-01NT41020 awarded by the Department of Energy. The Government has certain rights in this invention.