Shroud segment cooling configuration

Details Shroud segment cooling configuration Shroud segment cooling configuration

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F01D 25/12 (2006.01)

Patent

CA 2662042

An cooling arrangement for a turbine shroud provides an air stream directed from a passage extending through a radial wall to impinge on a surface in an area of a back side of the turbine shroud, the surface defining a plane which improves the attack angle of the air stream to the surface.

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