Rotating turbine component with preferential hole alignment

A turbine airfoil, comprising:

• a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip;
• an internal rib extending between the pressure sidewall and the suction sidewall;
• and a plurality of crossover holes formed in the internal rib, each hole of the plurality of crossover holes having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape;
• wherein the major axis of each hole of the plurality of crossover holes is non-parallel to said pressure sidewall and said suction sidewall,
• wherein said plurality of crossover holes comprises a radially inward-most crossover hole;
• said radially inward-most crossover hole oriented at a different angle from the remainder of said plurality of crossover holes, and
• wherein said radially inward-most crossover hole contains a major axis which is offset from a radial axis by an angle of about 15 degrees.

A turbine airfoil, comprising:

• a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip;
• an internal rib extending between the pressure sidewall and the suction sidewall;
• and a plurality of crossover holes formed in the rib, each hole of the plurality of crossover holes having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape;
• wherein the major axis of each hole of the plurality of crossover holes lies in plane with the rib and is non-parallel to a curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls,
• six cavities;
• and
• five ribs;
• wherein said plurality of crossover holes comprises a radially inward crossover hole;
• said radially inward crossover hole oriented at a different angle from the remainder of said plurality of crossover holes,
• wherein said radially inward crossover hole contains a major axis which is offset from said curvilinear lateral centerline by an angle of at least 10 degrees,
• wherein each of said five ribs comprises at least one crossover hole and forms a boundary of one or more of said six cavities;
• wherein each of said concave pressure sidewall and said convex suction sidewall forms a boundary of said six cavities:
• wherein each of said at least one crossover holes comprises a major axis;
• wherein the major axis of each of said at least one crossover holes is non-parallel to said curvilinear lateral centerline;
• and
• wherein said airfoil comprises no more than a single crossover hole at any radial location along each of said five ribs.