Cooling assembly for a turbine assembly

1. A cooling assembly comprising:

a coolant source chamber disposed inside an airfoil of a turbine assembly, the coolant source chamber configured to direct coolant inside the airfoil of the turbine assembly, the airfoil including a pressure side wall and a suction side wall, the airfoil configured to extend between a hub end of the airfoil and a tip end of the airfoil along a radial length of the airfoil, the tip end of the airfoil including a tip body and a tip rail;

a first body cooling chamber and a second body cooling chamber disposed inside the tip body of the airfoil, the first body cooling chamber and the second body cooling chamber extending from the pressure side wall to the suction side wall, wherein the second body cooling chamber is positioned between the tip rail and the first body cooling chamber along the radial length of the airfoil, at least one of the first and second body cooling chambers are fluidly coupled with the coolant source chamber, wherein the coolant source chamber is configured to direct at least some of the coolant into one or more of the first and second body cooling chambers; and

a rail cooling chamber disposed inside of the tip rail of the airfoil, the rail cooling chamber fluidly coupled with at least one of the first and second body cooling chambers, wherein the at least some of the coolant is directed out of at least one of the first and second body cooling chambers and into the rail cooling chamber.

2. The cooling assembly of claim 1 , further including one or more exhaust channels fluidly coupled with at least one of the rail cooling chamber and one or both of the first and second body cooling chambers, wherein the one or more exhaust channels are configured to direct the coolant out of the airfoil.

3. The cooling assembly of claim 1 , wherein the first body cooling chamber and the second body cooling chamber are configured to be elongated extending from an inner surface of the pressure side wall of the airfoil to an inner surface of the suction side wall of the airfoil.

4. The cooling assembly of claim 1 , wherein the first body cooling chamber is elongated along and encompasses at least part of a first axis and the second body cooling chamber is elongated along and encompasses at least part of a second axis different from the first axis, wherein the first axis and the second axis are either parallel or oblique to each other.

5. The cooling assembly of claim 4 , wherein the first axis is configured to extend in a direction perpendicular to the radial length of the airfoil, and wherein the second axis is configured to extend in a direction perpendicular to the radial length of the airfoil.

6. The cooling assembly of claim 1 , further including one or both of plural pins and plural turbulators disposed inside at least one of the first and second body cooling chambers, wherein the coolant is directed around the one or both-of the plural pins and the plural turbulators.

7. The cooling assembly of claim 1 , further including plural walls disposed inside at least one of the first and second body cooling chambers, wherein the coolant is directed around the plural walls.

8. The cooling assembly of claim 1 , wherein the rail cooling chamber is a first rail cooling chamber, and further including a second rail cooling chamber disposed inside the tip rail of the airfoil, wherein the first rail cooling chamber is fluidly coupled with the second rail cooling chamber.

9. The cooling assembly of claim 1 , further including a third body cooling chamber disposed inside the tip body of the airfoil, wherein the third body cooling chamber is fluidly coupled with the first and second body cooling chambers.

10. The cooling assembly of claim 1 , further including one or both of:

an impingement baffle separating the first body cooling chamber from the second body cooling chamber and fluidly coupling the first body cooling chamber and the second body cooling chamber; and

a serpentine circuit formed by a portion of the first body cooling chamber and a portion of the second body cooling chamber.

11. A cooling assembly comprising:

a coolant source chamber disposed inside an airfoil of a turbine assembly, the coolant source chamber configured to direct coolant inside the airfoil of the turbine assembly, the airfoil including a pressure side wall and a suction side wall, the airfoil configured to extend between a hub end of the airfoil and a tip end of the airfoil along a radial length of the airfoil, the tip end of the airfoil including a tip body and a tip rail;

a first body cooling chamber, a second body cooling chamber, and a third body cooling chamber disposed inside the tip body of the airfoil, the first body cooling chamber and the second body cooling chamber longitudinally extending from the pressure side wall to the suction side wall, wherein the second body cooling chamber is positioned between the tip rail and the first body cooling chamber along the radial length of the airfoil, at least one of the first and second body cooling chambers are fluidly coupled with the coolant source chamber, wherein the coolant source chamber is configured to direct at least some of the coolant into the at least one of the first and second body cooling chambers;

a rail cooling chamber disposed inside of the tip rail of the airfoil, the rail cooling chamber fluidly coupled with at least one of the first and second body cooling chambers, wherein at least some of the coolant is directed from the first and second body cooling chambers and into the rail cooling chamber; and

one or more exhaust channels fluidly coupled with at least one of the rail cooling chamber and one or both of the first and second body cooling chambers;

wherein the one or more exhaust channels are configured to direct at least some of the coolant out of the airfoil.

12. The cooling assembly of claim 11 , further including a pressure side wall inner surface of the airfoil and a suction side wall inner surface of the airfoil, wherein the first and second body cooling chambers are configured to be elongated extending from the pressure side wall inner surface of the airfoil to the suction side wall inner surface of the airfoil.

13. The cooling assembly of claim 11 , wherein the first body cooling chamber is elongated along and encompasses at least part of a first axis and the second body cooling chamber is elongated along and encompasses at least part of a second axis different from the first axis, wherein the first axis and the second axis are either parallel or oblique to each other.

14. The cooling assembly of claim 13 , wherein the first axis is configured to extend in a direction perpendicular to the radial length of the airfoil, and wherein the second axis is configured to extend in a direction perpendicular to the radial length of the airfoil.

15. The cooling assembly of claim 11 , further including one or both of plural pins and plural turbulators disposed inside at least one of the first and second body cooling chambers, wherein the coolant is directed around the one or both of the plural pins and the plural turbulators.

16. The cooling assembly of claim 11 , further including plural walls disposed inside at least one of the first and second body cooling chambers, wherein the coolant is directed around the plural walls inside the at least one of the first and second body cooling chambers.

17. The cooling assembly of claim 11 , wherein the rail cooling chamber is a first rail cooling chamber, and further including a second rail cooling chamber disposed inside the tip rail of the airfoil, wherein the first rail cooling chamber is fluidly coupled with the second rail cooling chamber.

18. The cooling assembly of claim 11 , wherein the third body cooling chamber is fluidly coupled with the first and second body cooling chambers.

19. The cooling assembly of claim 11 , further including one or both of:

an impingement baffle separating the first body cooling chamber from the second body cooling chamber and fluidly coupling the first body cooling chamber and the second body cooling chamber; and

a serpentine circuit formed by a portion of the first body cooling chamber and a portion of the second body cooling chamber.

20. A method comprising:

fluidly coupling at least one of a first body cooling chamber and a second body cooling chamber with a coolant source chamber disposed inside an airfoil, the first body cooling chamber and the second body cooling chamber disposed inside a tip body of the airfoil, the airfoil including a pressure side wall and a suction side wall, the airfoil configured to extend between a hub end of the airfoil and a tip end of the airfoil along a radial length of the airfoil, the tip end of the airfoil including the tip body and a tip rail, wherein the coolant source chamber is configured to direct coolant out of the coolant source chamber and into the at least one of the first and second body cooling chambers, the second body cooling chamber positioned between the tip rail and the first body cooling chamber along the radial length of the airfoil, the first body cooling chamber and the second body cooling chamber extending from the pressure side wall to the suction side wall; and

fluidly coupling a rail cooling chamber disposed inside the tip rail of the airfoil with at least one of the first and second body cooling chambers, wherein at least some of the coolant is directed out of at least one of the first and second body cooling chambers and into the rail cooling chamber.