Ventilated thermal barrier coating

摘要

A gas turbine engine component includes a perforate metal wall (32) having pores (40) extending therethrough. The wall (32) has a first surface (34) covered by a thermal barrier coating (38). The pores (40) have first ends (42) which are covered by the thermal barrier coating (38), and the pores (40) are ventilated from an opposite second surface (36) of the wall for cooling the thermal barrier coating (38). <IMAGE>