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Gas turbine power plant with supersonic shock compression ramps

United States Patent

October 14, 2008
View the Complete Patent at the US Patent & Trademark Office
A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdynamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by use of a lean pre-mix system, a pre-swirl compressor, and a bypass stream to bleed a portion of the gas after passing through the pre-swirl compressor to the combustion gas outlet. Use of a stationary low NOx combustor provides excellent emissions results.
Lawlor; Shawn P. (Bellevue, WA), Novaresi; Mark A. (San Diego, CA), Cornelius; Charles C. (Kirkland, WA)
11/ 102,937
March 30, 2005
STATEMENT OF GOVERNMENT INTEREST This invention was made with United States Government support under Contract No. DE-FC026-00NT40915 awarded by the United States Department of Energy. The U.S. Government has certain rights in the invention.