Cooled stationary blade for a gas turbine

Details Cooled stationary blade for a gas turbine Cooled stationary blade for a gas turbine

1998-03-11

2000-08-08

Look, Edward K.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

415116, 416 96R, 416 97R, F01D 508

Patent

active

060992441

ABSTRACT:
In the present invention, seal air passes through a tube extending in a stationary blade from an outside shroud to an inside shroud, flows into a cavity to keep the pressure in the cavity high so as to seal the high-temperature combustion gas, and is discharged to a passage. Part of cooling air flows into an air passage to cool the leading edge portion, passes through the peripheral portion of the inside shroud to cool the same, and is discharged to a passage. The remaining cooling air flows into a passage, passes through a serpentine cooling flow path consisting of air passages having turbulators, and is discharged through air cooling holes formed at the trailing edge. The cooling air passing through the passage at the leading edge portion cools the peripheral portion of the inside shroud as well as the leading edge portion of blade, by which the cooling efficiency is increased.

REFERENCES:
patent: 4616976 (1986-10-01), Lings et al.
patent: 4946346 (1990-08-01), Ito
patent: 5488825 (1996-02-01), Davis et al.
patent: 5609466 (1997-03-01), North et al.

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