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Serial cooling of a combustor for a gas turbine engine

United States Patent

November 13, 2001
View the Complete Patent at the US Patent & Trademark Office
A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding combustion air to a plurality of fuel nozzles. The flow diverting mechanism adjusts combustion air according to engine loading.
Abreu; Mario E. (Poway, CA), Kielczyk; Janusz J. (Escondido, CA)
Solar Turbines Incorporated (San Diego, CA)
09/ 465,026
December 16, 1999
"The Government of the United States of America has rights in this invention pursuant to Contract No. DE-FC21-95MC31173 awarded by the U.S. Department of Energy."