Turbine blade with reserve cooling air film hole direction

摘要

A gas turbine engine (10) includes turbine blades (50) having film cooling holes (36) at an outer face of an airfoil (34) wherein the film cooling holes (36) are designed to be better filled with air. In a disclosed embodiment, the film cooling holes (36) include a meter section (52) extending along a direction having a main component extending from a blade tip to a blade root. In addition, a diffused section (54) communicates with the meter section (52) at a face of the airfoil (34). The diffused section (54) is spaced toward the blade tip from the meter section (52). In this manner, centrifugal force ensures the diffused section (54) is also filled with air.