Shroud with aero-effective cooling

Details Shroud with aero-effective cooling Shroud with aero-effective cooling

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F01D 5/18 (2006.01) F01D 25/12 (2006.01)

Patent

CA 2554998

A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.

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