Flared crossovers for airfoils

1. An airfoil, comprising:

an airfoil section extending in a spanwise direction from a platform section, said airfoil section extending in a circumferential direction between a pressure side and a suction side, said airfoil section extending in an axial direction between a leading edge and a trailing edge, and said airfoil section having an external wall and an internal wall, said internal wall defining a reference plane extending in said spanwise direction along a surface of said internal wall;

a first cavity and a second cavity separated by said internal wall;

a plurality of crossover passages within said internal wall and connecting said first cavity to said second cavity, each of said plurality of crossover passages defining a passage axis, said plurality of crossover passages distributed in said spanwise direction and arranged such that said passage axis of each of said plurality of crossover passages intersects a surface of said second cavity, said second cavity being an impingement cooling cavity, and wherein said second cavity is bounded by said external wall; and

wherein said passage axis of each of said plurality of crossover passages is arranged at a radial angle relative to a localized region of said reference plane such that said radial angle of at least three of said plurality of crossover passages differs in said spanwise direction, said localized region defined at an intersection of said passage axis and said reference plane, and said radial angle defined such that a component of said passage axis extends in said spanwise direction.

2. The airfoil as recited in claim 1 , wherein said radial angle of each of said plurality of crossover passages changes in said spanwise direction.

3. The airfoil as recited in claim 1 , wherein said plurality of crossover passages are arranged such that said radial angle decreases as span position increases.

4. The airfoil as recited in claim 3 , wherein a projection of said passage axis of at least one of said plurality of crossover passages extends radially outward relative to said localized region of said reference plane.

5. The airfoil as recited in claim 1 , comprising a plurality of film cooling passages within said external wall and extending from said surface of said second cavity.

6. The airfoil as recited in claim 5 , wherein at least some of said plurality of film cooling passages define a first axis common with said passage axis of one of said plurality of crossover passages.

7. The airfoil as recited in claim 5 , wherein at least one of said plurality of film cooling passages defines a first axis arranged at a different radial angle relative to said localized region of said reference plane than said radial angle of at least one of said plurality of crossover passages.

8. The airfoil as recited in claim 1 , wherein said second cavity is bounded by one of a leading edge and a trailing edge of said airfoil section.

9. The airfoil as recited in claim 8 , wherein said radial angle of said at least three of said plurality of crossover passages progressively changes in said spanwise direction.

10. The airfoil as recited in claim 9 , wherein said at least three of said plurality of crossover passages includes four crossover passages.

11. The airfoil as recited in claim 1 , wherein said platform section defines at least one of said plurality of crossover passages.

12. The airfoil as recited in claim 1 , wherein said passage axis of at least one of said plurality of crossover passages is arranged at a first lateral angle relative to said localized region of said reference plane, and said passage axis of another one of said plurality of crossover passages is arranged at a second, different lateral angle relative to said localized region of said reference plane.

13. The airfoil as recited in claim 12 , wherein each of said first lateral angle and said second lateral angle is orthogonal to said radial angle of a respective one of said passage axis such that each said passage axis extends in said circumferential direction of said airfoil section with respect to said localized region of said reference plane.

14. The airfoil as recited in claim 1 , wherein a portion of said passage axis is curvilinear.

15. The airfoil as recited in claim 1 , wherein a cross-sectional area of at least one of said plurality of crossover passages is different than a cross-sectional area of another one of said plurality of crossover passages.

16. The airfoil as recited in claim 1 , wherein each of said plurality of crossover passages includes an inlet port and an outlet port, a pressure drop being defined by a pressure at said inlet port and a pressure at said outlet port, and said radial angle of each of said plurality of crossover passages is defined such that said pressure drop is less than or equal to a predetermined threshold.

17. The airfoil as recited in claim 16 , wherein said plurality of crossover passages includes a first set of crossover passages and a second set of crossover passages, said first set of crossover passages are arranged such that said radial angle decreases as span position increases, and said second set of crossover passages are arranged such that said radial angle increases as span position increases.

18. A casting core for an airfoil, comprising:

a first portion corresponding to a first cavity of an airfoil section and a second portion corresponding to a second cavity of the airfoil section, the airfoil section extending in a spanwise direction from a platform section, each of said first portion and said second portion extending in said spanwise direction, said first portion defining a reference plane in said spanwise direction along a surface of said first portion, said second cavity being an impingement cooling cavity, and wherein said second cavity is bounded by an external wall of said airfoil section;

a plurality of connectors coupling said first portion and said second portion, said plurality of connectors corresponding to a plurality of crossover passages of the airfoil, each of said plurality of connectors defining a first axis, said plurality of connectors being distributed in said spanwise direction; and

wherein said first axis of each of said plurality of connectors is arranged at a radial angle relative to a localized region of said reference plane such that said radial angle of at least three of said plurality of connectors differs in said spanwise direction, said localized region defined at an intersection of said first axis and said reference plane, and said radial angle defined such that a component of said first axis extends in said spanwise direction.

19. The casting core for an airfoil as recited in claim 18 , wherein said plurality of connectors are arranged such that said radial angle of each of said plurality of connectors decreases as span position increases relative to an inlet portion of said first portion.

20. A gas turbine engine, comprising:

a rotor and a vane spaced axially from said rotor with respect to an engine axis; and

wherein at least one of said rotor and said vane includes an airfoil section extending in a spanwise direction from a platform section, said spanwise direction extending radially from said engine axis, said airfoil section comprising:

an external wall and an internal wall defining a reference plane extending in said spanwise direction along a surface of said internal wall;

a first cavity and a second cavity separated by said internal wall, said second cavity being an impingement cooling cavity, and wherein said second cavity is bounded by said external wall;

a plurality of crossover passages within said internal wall and connecting said first cavity to said second cavity, each of said plurality of crossover passages defining a passage axis, said plurality of crossover passages distributed in said spanwise direction and arranged such that said passage axis of each of said plurality of crossover passages intersects a surface of said second cavity; and

wherein said passage axis of each of said plurality of crossover passages is arranged at a radial angle relative to a localized region of said reference plane such that said radial angle of at least three of said plurality of crossover passages differs in said spanwise direction, said localized region defined at an intersection of said passage axis and said reference plane, and said radial angle defined such that a component of said passage axis extends in said spanwise direction.

21. The gas turbine engine as recited in claim 20 , wherein said plurality of crossover passages are arranged such that said radial angle decreases as span position increases relative to said platform.

22. The gas turbine engine as recited in claim 20 , wherein said plurality of crossover passages includes a first set of crossover passages and a second set of crossover passages, said first set of crossover passages are arranged such that said radial angle decreases as span position increases, and said second set of crossover passages are arranged such that said radial angle increases as span position increases.

23. The gas turbine engine as recited in claim 20 , wherein said at least three of said plurality of crossover passages includes four crossover passages, and wherein said radial angle of said four plurality of crossover passages progressively changes in said spanwise direction.