发明名称 |
GAS TURBINE POWER PLANT WITH SUPERSONIC GAS COMPRESSOR |
摘要 |
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 gasdyanamic 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. |
申请公布号 |
WO2004029432(A3) |
申请公布日期 |
2004.08.12 |
申请号 |
WO2003US30609 |
申请日期 |
2003.09.25 |
申请人 |
RAMGEN POWER SYSTEMS, INC. |
发明人 |
LAWLOR, SHAWN, P.;NOVARESI, MARK, A.;CORNELIUS, CHARLES, C. |
分类号 |
F01D1/34;F02C3/08;F02C6/02;F02K7/10;F04D21/00 |
主分类号 |
F01D1/34 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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