Turbine rotor blade with angel wing with coolant transfer passage between adjacent wheel space portions by additive manufacture

1. A turbine rotor blade, comprising:

an airfoil body including a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges;

a shank at a radial inner end of the airfoil body;

at least one angel wing extending laterally from at least one side of the shank; and

a coolant transfer passage defined through the at least one angel wing, the coolant transfer passage fluidly coupling a first wheel space portion defined between the shank and a first adjacent shank of a first adjacent turbine rotor blade and a second wheel space portion defined between the shank and a second adjacent shank of a second adjacent turbine rotor blade.

2. The turbine rotor blade of claim 1 , wherein the coolant transfer passage includes a first open end in fluid communication with the first wheel space portion and a second open end in fluid communication with the second wheel space portion, wherein the first open end and the second open end face in a circumferential direction relative to the airfoil body.

3. The turbine rotor blade of claim 1 , wherein the outer walls define a radially extending chamber that extends into the shank, and wherein the coolant transfer passage is fluidly isolated from the radially extending chamber.

4. The turbine rotor blade of claim 1 , wherein the at least one angel wing extending laterally from the at least one side of the shank includes a first pair of radially spaced angel wings extending laterally from a first side of the shank, each angel wing of the first pair including a respective coolant transfer passage.

5. The turbine rotor blade of claim 4 , wherein the at least one angel wing extending laterally from the at least one side of the shank includes a second pair of radially spaced angel wings extending laterally from a second, opposing side of the shank, each angel wing of the second pair including a respective coolant transfer passage.

6. The turbine rotor blade of claim 1 , wherein the at least one angel wing extending laterally from the at least one side of the shank includes a first angel wing extending laterally from a first side of the shank and a second angel wing extending laterally from a second, opposing side of the shank, each of the first and second angel wings including a respective coolant transfer passage.

7. An additively manufactured turbine rotor blade, comprising:

an airfoil body including a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges;

a shank at a radial inner end of the airfoil body;

at least one angel wing extending laterally from at least one side of the shank; and

a coolant transfer passage defined through the at least one angel wing, the coolant transfer passage fluidly coupling a first wheel space portion defined between the shank and a first adjacent shank of a first adjacent turbine rotor blade and a second wheel space portion defined between the shank and a second adjacent shank of a second adjacent turbine rotor blade.

8. The additively manufactured turbine rotor blade of claim 7 , wherein the coolant transfer passage includes a first open end in fluid communication with the first wheel space portion and a second open end in fluid communication with the second wheel space portion, wherein the first open end and the second open end face in a circumferential direction relative to the airfoil body.

9. The additively manufactured turbine rotor blade of claim 7 , wherein the outer walls define a radially extending chamber that extends into the shank, and wherein the coolant transfer passage is fluidly isolated from the radially extending chamber.

10. The additively manufactured turbine rotor blade of claim 7 , wherein the at least one angel wing extending laterally from the at least one side of the shank includes a first pair of radially spaced angel wings extending laterally from a first side of the shank, each angel wing of the first pair including a respective coolant transfer passage.

11. The additively manufactured turbine rotor blade of claim 10 , wherein the at least one angel wing extending laterally from the side of the shank includes a second pair of radially spaced angel wings extending laterally from a second, opposing side of the shank, each angel wing of the second pair including a respective coolant transfer passage.

12. The additively manufactured turbine rotor blade of claim 7 , wherein the at least one angel wing extending laterally from the at least one side of the shank includes a first angel wing extending laterally from a first side of the shank and a second angel wing extending laterally from a second, opposing side of the shank, each of the first and second angel wings including a respective coolant transfer passage.

13. A set of turbine rotor blades, comprising:

a first turbine rotor blade, a second turbine rotor blade and a third turbine rotor blade, the first turbine rotor blade positioned between the second and third turbine rotor blades, each turbine rotor blade including:

an airfoil body including a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges,

a shank at a radial inner end of the airfoil body, and

at least one angel wing extending laterally from at least one side of the shank,

wherein the shanks of the first and second turbine rotor blades define a first wheel space portion therebetween and the shanks of the first and third turbine rotor blades define a second wheel space portion therebetween; and

a coolant transfer passage defined through the at least one angel wing in the first turbine rotor blade, the coolant transfer passage fluidly coupling the first wheel space portion and the second wheel space portion.

14. The set of turbine rotor blades of claim 13 , wherein the coolant transfer passage includes a first open end in fluid communication with the first wheel space portion and a second open end in fluid communication with the second wheel space portion, and wherein the first open end and the second open end face in a circumferential direction relative to the airfoil body of the first turbine rotor blade.

15. The set of turbine rotor blades of claim 13 , wherein the outer walls define a radially extending chamber that extends into the shank of the first rotor blade, and wherein the coolant transfer passage is fluidly isolated from the radially extending chamber.

16. The set of turbine rotor blades of claim 13 , wherein the at least one angel wing extending laterally from the at least one side of the shank of the first turbine rotor blade includes a first pair of radially spaced angel wings extending laterally from a first side of the shank, each angel wing of the first pair including a respective coolant transfer passage.

17. The set of turbine rotor blades of claim 16 , wherein the at least one angel wing extending laterally from the at least one side of the shank of the first turbine rotor blade includes a second pair of radially spaced angel wings extending laterally from a second, opposing side of the shank, each angel wing of the second pair including a respective coolant transfer passage.

18. The set of turbine rotor blades of claim 13 , wherein the at least one angel wing extending laterally from the at least one side of the shank of the first turbine rotor blade includes a first angel wing extending laterally from a first side of the shank and a second angel wing extending laterally from a second, opposing side of the shank, each of the first and second angel wings including a respective coolant transfer passage.

19. The set of turbine rotor blades of claim 13 , wherein the at least one angel wing of the second and third turbine rotor blades each include a coolant transfer passage defined therethrough, the coolant transfer passage fluidly coupling wheel space portions on opposing sides of the shank of each respective turbine rotor blade.