Methods and system for recuperated circumferential cooling...

Details Methods and system for recuperated circumferential cooling... Methods and system for recuperated circumferential cooling...

2006-11-30

2009-10-20

Nguyen, Ninh N (Department: 3745)

Rotary kinetic fluid motors or pumps

Method of operation

C415S173100, C415S199500

Reexamination Certificate

active

07604453

ABSTRACT:
A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface.

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