Engine with cooling passage circuit extending through blade, seal, and ceramic vane

1. A gas turbine engine comprising:

a rotor carrying a blade;

a ceramic vane adjacent the blade, the ceramic vane having a tip;

a seal carried on the rotor adjacent the tip of the ceramic vane; and

a cooling passage circuit extending through the blade, the seal, and the ceramic vane, the cooling passage circuit configured to provide cooling air into the blade, then from the blade into the seal, and then from the seal into the ceramic vane, wherein the blade includes a compliant passage seal sealing a supply passage into the blade from a return passage that connects the supply passage with the seal.

2. The gas turbine engine as recited in claim 1 , wherein the cooling passage circuit includes a circuit leg in the seal, the circuit leg including an axial passage connected to receive cooling air from the blade, and a radial feed passage connecting the axial passage with the ceramic vane.

3. The gas turbine engine as recited in claim 1 , wherein the seal is formed of ceramic.

4. The gas turbine engine as recited in claim 3 , wherein the rotor includes a disk and an axial support arm projecting from the disk and supporting the seal.

5. The gas turbine engine as recited in claim 3 , wherein the rotor includes a disk supporting the seal.

6. The gas turbine engine as recited in claim 1 , wherein the cooling passage circuit includes a radial inlet in the tip of the ceramic vane and a radial outlet in the seal which is in register with the radial inlet, the tip of the ceramic vane has forward and aft vane seal elements, the radial inlet is axially between the forward and aft vane seal elements, the seal has forward and aft mating seal elements, and the radial outlet is axially between the forward and aft mating seal elements.

7. The gas turbine engine as recited in claim 1 , wherein the cooling passage circuit includes a circuit leg in the blade, the circuit leg includes an inlet, an axially-extending manifold passage, one or more radially-extending supply passages, and one or more return passages connecting the one or more radially-extending supply passages to an inlet and an axial passage in the seal.

8. The gas turbine engine as recited in claim 7 , where the compliant passage seal is disposed in the axially-extending manifold passage.

9. The gas turbine engine as recited in claim 7 , wherein the compliant passage seal is disposed in a rib that projects radially inwardly from a root of the blade.

10. A gas turbine engine comprising:

a forward stage including a row of forward vanes followed by a row of forward blades;

an aft stage including a row of aft ceramic vanes followed by a row of aft blades, the aft ceramic vanes having respective tips;

seals adjacent the tips of the aft ceramic vanes; and

a cooling passage circuit extending through the forward blades, the seals, and the aft ceramic vanes, the cooling passage circuit including radial inlets in the tips of the aft ceramic vanes and radial outlets in the seals which are in register with the radial inlets, the tips of the aft ceramic vanes having forward and aft vane seal elements, the radial inlets being axially between the forward and aft vane seal elements, the seals having forward and aft mating seal elements, and the radial outlets being axially between the forward and aft mating seal elements.

11. The gas turbine engine as recited in claim 10 , wherein the forward stage is a first turbine stage and the aft stage is a second turbine stage.

12. The gas turbine engine as recited in claim 10 , further comprising a cooling air source radially inwards of the forward blades.

13. The gas turbine engine as recited in claim 10 , wherein the cooling passage circuit is configured to provide cooling air into the forward blades, then from the forward blades into the seals, and then from the seals into the aft ceramic vanes.

14. The gas turbine engine as recited in claim 13 , wherein the cooling passage circuit includes a circuit leg in the forward blades, the circuit leg including supply passages into the forward blades and return passages connecting the supply passages with the seals.

15. The gas turbine engine as recited in claim 13 , wherein the cooling passage circuit includes a circuit leg in the seals, the circuit leg including axial passages connected to receive cooling air from the forward blades, and radial feed passages connecting the axial passages with the aft ceramic vanes.

16. The gas turbine engine as recited in claim 13 , wherein the cooling passage circuit includes first and second circuit legs, the first circuit leg being in the forward blades and including supply passages into the forward blades and return passages connecting the supply passages with the seals, and the second circuit leg being in the seals and including axial passages connected to receive cooling air from the return passages, and radial feed passages connecting the axial passages with the aft ceramic vanes.

17. The gas turbine engine as recited in claim 10 , wherein the seals are formed of ceramic.

18. The gas turbine engine as recited in claim 10 , wherein each of the forward blades includes a compliant passage seal that seals a supply passage of the cooling passage circuit into each forward blade from a return passage of the cooling passage circuit that connects the supply passage with the compliant passage seal.