CMC vane with support spar and baffle

1. A vane for a gas turbine engine, comprising:

a ceramic airfoil section having an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side, the ceramic airfoil section having an internal cavity;

a support spar extending through the internal cavity for supporting the ceramic airfoil section, the support spar being spaced from the airfoil wall such that there is a gap there between, the support spar having an internal through-passage that is fluidly isolated from the gap in the ceramic airfoil section; and

a baffle disposed in the gap, the baffle being spaced apart from the airfoil wall and the support spar so as to divide the gap into a plenum space between the support spar and the baffle and an impingement space between the baffle and the airfoil wall, the baffle having impingement holes directed toward the airfoil wall and connecting the plenum space and the impingement space.

2. The vane as recited in claim 1 , wherein the baffle circumscribes the support spar.

3. The vane as recited in claim 1 , wherein the baffle defines first and second ends, and the second end is sealed with the support spar and is sealed with the airfoil wall such that the impingement holes are an exclusive exit from the plenum space.

4. The vane as recited in claim 3 , wherein the baffle is sealed with the airfoil wall by a seal member and is sealed with the support spar by a weld joint.

5. The vane as recited in claim 1 , wherein the baffle is formed of sheet metal.

6. The vane as recited in claim 1 , wherein the baffle is mounted on a spring member.

7. The vane as recited in claim 1 , wherein the support spar is formed of a single-crystal metal alloy.

8. The vane as recited in claim 1 , wherein the impingement holes are directed toward the leading edge.

9. The vane as recited in claim 1 , wherein the airfoil section includes a rib that divides the internal cavity into a forward cavity that is bounded by the leading edge and an aft cavity that is bounded by the trailing edge, and the support spar and the baffle are disposed in the forward cavity.

10. The vane as recited in claim 1 , wherein the internal through-passage conveys first pressurized air through the ceramic airfoil section, and the plenum space conveys second, different pressurized air that discharges through the impingement holes onto the airfoil wall.

11. A vane for a gas turbine engine, comprising:

a ceramic airfoil section having an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side, the ceramic airfoil section having an internal cavity bounded at least by the leading edge;

a support spar extending through the internal cavity for supporting the ceramic airfoil section, the support spar being spaced from leading edge such that there is a gap there between, the support spar having an internal through-passage that is fluidly isolated from the gap in the ceramic airfoil section, the internal through-passage conveying first pressurized air through the ceramic airfoil section; and

a baffle disposed in the gap, the baffle being spaced apart from the airfoil wall and the support spar so as to divide the gap into a plenum space between the support spar and the baffle and an impingement space between the baffle and the airfoil wall, the baffle having impingement holes directed toward the leading edge of the airfoil wall and connecting the plenum space and the impingement space, the plenum space conveying second, different pressurized air that discharges through the impingement holes onto the leading edge of the airfoil wall.

12. The vane as recited in claim 11 , wherein the first pressurized air and the second pressurized air differ in Mach number.

13. The vane as recited in claim 11 , wherein the Mach number of the first pressurized air is greater than the Mach number of the second pressurized air.

14. The vane as recited in claim 11 , wherein the baffle circumscribes the support spar.

15. The vane as recited in claim 14 , wherein the baffle defines first and second ends, and the second end is sealed with the support spar and is sealed with the airfoil wall such that the impingement holes are an exclusive exit from the plenum space.

16. The vane as recited in claim 15 , wherein the baffle is sealed with the airfoil wall by a seal member and is sealed with the support spar by a weld joint.

17. The vane as recited in claim 16 , wherein the support spar is formed of a single-crystal metal alloy.

18. The vane as recited in claim 17 , wherein the baffle is formed of sheet metal.

19. The vane as recited in claim 18 , wherein the baffle is mounted on a spring member.

20. A gas turbine engine comprising:

a compressor section;

a combustor in fluid communication with the compressor section; and

a turbine section in fluid communication with the combustor, the turbine section having a vane that includes:

a ceramic airfoil section having an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side, the ceramic airfoil section having an internal cavity,

a support spar extending through the internal cavity for supporting the ceramic airfoil section, the support spar being spaced from the airfoil wall such that there is a gap there between, the support spar having an internal through-passage that is fluidly isolated from the gap in the ceramic airfoil section, and

a baffle disposed in the gap, the baffle being spaced apart from the airfoil wall and the support spar so as to divide the gap into a plenum space between the support spar and the baffle and an impingement space between the baffle and the airfoil wall, the baffle having impingement holes directed toward the airfoil wall and connecting the plenum space and the impingement space.