Turbine shroud segment apparatus for reusing cooling air

Rotary kinetic fluid motors or pumps – With diversely oriented inlet or additional inlet for...

Reexamination Certificate

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Details

C415S173100, C415S178000

Reexamination Certificate

active

06899518

ABSTRACT:
A cooled turbine shroud segment for a gas turbine engine, having an axially extending shroud ring segment with an inner surface, an outer surface, an upstream flange and a downstream flange. The flanges mount the shroud ring within an engine casing. A perforated cooling air impingement plate is disposed on the outer surface of the shroud ring between the upstream flange and the downstream flange, with an impingement plenum defined between the impingement plate and the outer surface. Axially extending cooling bores in the ring segment extend between the impingement plenum and an outlet. A trough adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.

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