Gas turbine vane with a cooled inner shroud

Details Gas turbine vane with a cooled inner shroud Gas turbine vane with a cooled inner shroud

1995-11-27

1997-03-11

Look, Edward K.

Rotary kinetic fluid motors or pumps

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

416 96A, F01D 904, F01D 906

Patent

active

056094663

ABSTRACT:
A gas turbine vane having an inner shroud that is cooled by a portion of the cooling air directed to a cavity between two adjacent rows of discs. A portion of the cooling air in the cavity flows through impingement plates and impinges on the inner surface of the inner shroud. Another portion of the cooling air flows through a passage in the leading edge of the inner shroud that has a pin fin array for enhanced cooling. The impingement plates form chambers that collect both the impingement air and the pin fin passage air and direct it through holes in the trailing edge of the inner shroud for cooling of the trailing edge. Longitudinal passages along the side of the inner shroud direct the cooling air from the pin fin passage tot the trailing edge.

REFERENCES:
patent: 4474532 (1984-10-01), Pazder
patent: 4902198 (1990-02-01), North
patent: 4930980 (1990-06-01), North et al.
patent: 4962640 (1990-10-01), Tobery
patent: 5358374 (1994-10-01), Correia et al.
patent: 5399065 (1995-03-01), Kudo et al.
patent: 5413458 (1995-09-01), Calderbank
patent: 5488825 (1996-02-01), Davis et al.

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