Film cooled wall with chevron-shaped cooling holes

摘要

A wall (32) in a gas turbine engine includes inner and outer surfaces (34,36) having a row of compound chevron film cooling holes (38) extending therethrough. The chevron holes (38) diverge both longitudinally and laterally between an inlet at the wall inner surface (34) and a chevron outlet (42) at the wall outer surface (36). Each of said chevron holes includes a cylindrical inlet bore (44) commencing at said inlet in said inner surface and terminates in a pair of wing troughs (48) having a common ridge (50) therebetween.