ROTATING TURBINE COMPONENT WITH PREFERENTIAL HOLE ALIGNMENT

摘要

A turbine airfoil (22) includes: a concave pressure sidewall (50) and a convex suction sidewall (52) joined together at a leading edge (54) and a trailing edge (56), and extending between a root (53) and a tip (55); an internal rib (72) extending between the pressure sidewall (50) and the suction sidewall (52); and a crossover hole (84) formed in the rib (72), the crossover hole (84) having a noncircular cross-sectional shape with a major axis (M) defining a maximum dimension of the cross-sectional shape; wherein the major axis (M) of the crossover hole (84) lies in plane with the rib (72) and is non- parallel to an imaginary curvilinear lateral centerline (S) which defines a locus of points lying halfway between the pressure and suction sidewalls (50, 52). The orientation of the crossover holes (84) minimizes stress concentration caused by the presence of the crossover holes (84).