Gas turbine cooling system

Details Gas turbine cooling system Gas turbine cooling system

2005-01-11

2005-01-11

Look, Edward K. (Department: 3745)

Rotary kinetic fluid motors or pumps

With diversely oriented inlet or additional inlet for...

C416S09700R

Reexamination Certificate

active

06840737

ABSTRACT:
A stage of guide vanes (20) are cooled by compressor air delivered via piping (36,38) and by leakage air in the space volume (28) bounded by the combustion apparatus (14) and turbine shafting. The leakage air is drawn through tubing (40) by the compressor air which is directed over the exit ends of tubing (40) to create the necessary pressure drop in the tubing (40).

REFERENCES:
patent: 3628880 (1971-12-01), Smuland et al.
patent: 3663118 (1972-05-01), Johnson
patent: 4126405 (1978-11-01), Bobo et al.
patent: 4257734 (1981-03-01), Guy et al.
patent: 5167486 (1992-12-01), Detanne
patent: 5224818 (1993-07-01), Drerup et al.
patent: 5232338 (1993-08-01), De Paul
patent: 2189845 (1987-11-01), None

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