Title:
GAS TURBINE POWER PLANT WITH SUPERSONIC GAS COMPRESSOR
Document Type and Number:
WIPO Patent Application WO2004029432
Kind Code:
A3
Abstract:
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.
Inventors:
LAWLOR SHAWN P
NOVARESI MARK A
CORNELIUS CHARLES C
NOVARESI MARK A
CORNELIUS CHARLES C
Application Number:
PCT/US2003/030609
Publication Date:
August 12, 2004
Filing Date:
September 25, 2003
Export Citation:
Assignee:
RAMGEN POWER SYSTEMS INC (US)
International Classes:
F01D1/34; F02C3/08; F02C6/02; F02K7/10; F04D21/00; (IPC1-7): F02C3/04
Foreign References:
| US6446425B1 | 2002-09-10 | |||
| US6694743B2 | 2004-02-24 | |||
| US6279309B1 | 2001-08-28 | |||
| US6298653B1 | 2001-10-09 | |||
| US2623688A | 1952-12-30 | |||
| US20020073714A1 | 2002-06-20 | |||
| US5782079A | 1998-07-21 | |||
| US4408957A | 1983-10-11 | |||
| US3719426A | 1973-03-06 | |||
| US3422625A | 1969-01-21 | |||
| US2805818A | 1957-09-10 | |||
| US3541790A | 1970-11-24 |
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