Title:
GAS TURBINE ENGINE
Document Type and Number:
WIPO Patent Application WO2000020739
Kind Code:
A9
Abstract:
A gas turbine engine comprises a turbine (10), a compressor turbine (14) mounted downstream the turbine (10) for rotation in a direction opposite to the rotation direction of the turbine (10) that is mounted downstream the compressor (12). Exhaust fluid from the compressor turbine (14) is cooled in a heat exchanger (24) with a compressed fluid downstream the compressor (12) and is then cooled with air in separate heat exchanger (26) before being admitted to the compressor (12). A part (25.1) of the compressed fluid heated in the heat exchanger (24) is fed to cool the turbine blades, and the rest (25.2) of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor (30) and is discharged from the engine. The booster compressor (30) is driven by an expanding turbine (32) that is rotated under the effect of combustion air that is expanded in the expanding turbine (32) and flows through the expanding turbine (32) under the action of reduced pressure in the heated fluid source.
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Inventors:
RAKHMAILOV ANATOLY
Application Number:
PCT/US1999/020885
Publication Date:
July 05, 2001
Filing Date:
September 24, 1999
Export Citation:
Assignee:
ALM DEV INC (US)
International Classes:
F02C6/00; (IPC1-7): F02C6/00; F02C3/10; F02C3/34; F02C7/18
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