Turbine nozzle cooling

Details Turbine nozzle cooling Turbine nozzle cooling

1989-12-11

1994-01-25

Bertsch, Richard A.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

F02G 100

Patent

active

052807037

ABSTRACT:
Difficulties in cooling the vanes or blades (46) making up a turbine nozzle (40) in a gas turbine may be minimized or eliminated by placing interior passages (62) of the blades or vanes (46) in fluid communication with the compressor (14) and providing outlet passages (64) for the passages (62) in the rear turbine shroud (42). The passages (64) are preferably angled so that their downstream ends (68) open downstream. Consequently, eductor or ejector-like formations are present and when cooling air for a combustor (30) flowing in a cooling air path (28) passes across the ends (68), a region of lower pressure is formed to positively assure the flow of cooling air through the vanes or blades (46).

REFERENCES:
patent: 2709893 (1955-06-01), Birmann
patent: 2924937 (1960-02-01), Leibach
patent: 3304713 (1967-02-01), Sydlowski
patent: 3316714 (1967-05-01), Smith et al.
patent: 3623318 (1971-11-01), Shank
patent: 3797236 (1974-03-01), Hooke et al.
patent: 4173120 (1979-11-01), Grosjean et al.

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