Leakage air systems for turbomachines

1. A cooling system for a turbomachine, comprising:

a vane, including:

an outer diameter platform at one end including outer diameter attachment structure operative to mount the vane to an outer diameter stationary structure, the outer diameter attachment structure having leakage metering outlets formed therein;

an outer diameter cavity defined by the outer diameter platform and an outer diameter component;

an inner diameter platform at another end of the vane opposite the outer diameter platform and operative to be disposed against an inner diameter component;

an inner diameter cavity defined by the inner diameter platform and the inner diameter component; and

an airfoil disposed between the outer diameter platform and the inner diameter platform and defining a first cross-passage, wherein the first cross-passage defines a first outer diameter opening in the outer diameter platform, wherein the first cross-passage defines a first inner diameter opening in the inner diameter platform such that a first leakage flow can pass through the vane from the inner diameter platform, through the airfoil, to the outer diameter platform, and into an outer diameter leakage path of the vane, wherein the outer diameter leakage path is defined through the leakage metering outlets of the outer diameter attachment structure; and

a second cross-passage within the airfoil arranged such that a second leakage flow can pass through the vane from the outer diameter platform, through the airfoil, and to the inner diameter platform, wherein the first leakage flow and the second leakage flow are fluidly separated when passing through the vane,

wherein the second cross-passage extends between a second outer diameter opening and a second inner diameter opening such that the second leakage flow passes through the vane from the outer diameter platform to the inner diameter cavity and into an inner diameter leakage path of the vane.

2. The system of claim 1 , wherein the outer diameter component is a cover plate that is disposed on the outer diameter platform, the cover plate defining a leakage transfer cavity to guide the first leakage flow to the leakage metering outlets.

3. The system of claim 1 , wherein the inner diameter component is a cover plate that is disposed on the inner diameter platform.

4. The system of claim 1 , wherein the inner diameter component is an inner diameter stationary structure that is disposed on the inner diameter platform.

5. The system of claim 1 , wherein the airfoil includes additional cooling passages in fluid communication with vane outlets for allowing flow to exit from the airfoil directly into a gas path.

6. The system of claim 1 , wherein the outer diameter leakage path is between a pair of outer diameter feather seals of the outer diameter platform.

7. The system of claim 1 , wherein the outer diameter opening is disposed between attachment structure and in fluid communication with the outer diameter leakage path.

8. The system of claim 1 , wherein the second outer diameter opening is upstream of the outer diameter attachment structure relative to a gas path.

9. The system of claim 1 , wherein the second outer diameter opening is axially in between the outer diameter attachment structure.

10. The system of claim 1 , further comprising a turbine cooling air (TCA) pipe in fluid communication with the second outer diameter opening.

11. The system of claim 1 , wherein the inner diameter component is an inner diameter stationary structure that includes an inner air seal having an inner air seal cooling inlet.

12. The system of claim 11 , further including a transfer tube operatively coupled to the inner air seal cooling inlet and the first inner diameter opening, such that the second inner diameter opening is isolated from the first inner diameter opening.

13. The system of claim 1 , wherein the first cross-passage and the second cross-passage can be dimensioned and/or positioned to increase a temperature of leakage flow up to, but not including, a material failure temperature of a component associated with the vane.

14. A method for cooling a component of a turbomachine, comprising:

passing a first leakage flow from an inner diameter to an outer diameter of a vane through a first cross-passage;

leaking the first leakage flow through an outer diameter leakage path into a gas path after passing the first leakage flow through an airfoil of the vane, the outer diameter leakage path passing through leakage metering outlets formed in an outer diameter attachment structure operative to mount the vane to an outer diameter stationary structure;

passing a second leakage flow from the outer diameter to the inner diameter of the vane through a second cross-passage, wherein the first leakage flow and the second leakage flow are fluidly separated when passing through the vane,

passing the second leakage flow through the airfoil of the vane in the opposite direction of the first leakage flow and leaking the flow, and

isolating the first leakage flow from the second leakage flow.

15. The method of claim 14 , further comprising allowing the first leakage flow to heat up to, but not including, a material failure temperature of a component associated with the vane.

16. The method claim 14 , further comprising:

and leaking the second leakage flow through an inner diameter leakage path into the gas path after passing the second leakage flow through the airfoil of the vane.

17. The method of claim 16 , further comprising allowing the first leakage flow and/or second leakage flow to heat up to, but not including, a material failure temperature of a component associated with the vane.

18. A cooling system for a turbomachine, comprising:

a vane, including:

an outer diameter platform at one end including outer diameter attachment structure operative to mount the vane to an outer diameter stationary structure, the outer diameter attachment structure having leakage metering outlets formed therein;

an outer diameter cavity defined by the outer diameter platform and an outer diameter component;

an inner diameter platform at another end of the vane opposite the outer diameter platform and operative to be disposed against an inner diameter component;

an inner diameter cavity defined by the inner diameter platform and the inner diameter component; and

an airfoil disposed between the outer diameter platform and the inner diameter platform and defining a first cross-passage, wherein the first cross-passage defines a first outer diameter opening in the outer diameter platform, wherein the first cross-passage defines a first inner diameter opening in the inner diameter platform such that a first leakage flow can pass through the vane from the inner diameter platform, through the airfoil, to the outer diameter platform, and into an outer diameter leakage path of the vane, wherein the outer diameter leakage path is defined through the leakage metering outlets of the outer diameter attachment structure; and

a second cross-passage within the airfoil arranged such that a second leakage flow can pass through the vane from the outer diameter platform, through the airfoil, and to the inner diameter platform, wherein the first leakage flow and the second leakage flow are fluidly separated when passing through the vane,

wherein the inner diameter component is an inner diameter stationary structure that is disposed on the inner diameter platform.