GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE

摘要

A gas turbine engine (20) blade (64) includes a platform (68) that has an inner side (68A) and an outer side (68B), a root (70) that extends outwardly from the inner side (68A), and an airfoil (72) that extends outwardly from a base (72A) at the outer side (68B) to a tip end (72B). The airfoil (72) includes a leading edge and a trailing edge and a first side wall (72C) and a second side wall (72D). The first side wall (72C) and the second side wall (72D) join the leading edge and the trailing edge and at least partially define one or more cavities (74) in the airfoil (72). The airfoil (72) has a span from the base (72A) to the tip end (72B), with the base (72A) being at 0% of the span and the tip end (72B) being at 100% of the span. The first side wall (72C) includes an axial row (76) of cooling holes (78) at 90% or greater of the span.