Methods and apparatus for cooling gas turbine engine components

Details Methods and apparatus for cooling gas turbine engine components Methods and apparatus for cooling gas turbine engine components

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 25/12 (2006.01) F02C 7/12 (2006.01)

Patent

CA 2525283

A gas turbine engine component (40) includes a substrate wall (50) including a first surface (52) and an opposite second surface (54), and a plurality of pores (56) extending through the wall. The component also includes a thermal barrier coating (TBC) (74) extending over the wall first surface, wherein the TBC substantially seals the pores at the first surface. The component also includes a plurality of film cooling holes (58) extending through the wall and the TBC, wherein the plurality of film cooling holes and the plurality of pores extend substantially perpendicularly through the wall and the TBC.

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