METHODS AND APPARATUS FOR COOLING GAS TURBINE ENGINE COMPONENTS

摘要

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 perpendicularl y through the wall and the TBC.