Turbine vane with load shield
A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform. The airfoil includes a ceramic-containing web that forms a portion of the airfoil and a metallic load shield that forms another portion of the airfoil.
1. A turbine vane for use in a gas turbine engine, the turbine vane comprising
an inner platform,
an outer platform spaced from the inner platform, and
an airfoil that extends from the inner platform to the outer platform, the airfoil including a ceramic-containing web that forms a pressure side of the airfoil and a metallic load shield that forms a suction side of the airfoil and extends from a leading edge of the airfoil to a trailing edge of the airfoil,
wherein a cooling channel is formed between the ceramic-containing web and the metallic load shield that extends from a mid-span region of the airfoil toward the trailing edge of the airfoil.
2. The turbine vane of claim 1 , wherein the ceramic-containing web is formed to include a first plenum that extends across at least a portion of the distance from the inner platform to the outer platform and the first plenum is in fluid communication with the cooling channel to provide a pathway for cooling air in the first plenum to be conducted to the cooling channel during use of the turbine vane in the gas turbine engine.
3. The turbine vane of claim 2 , wherein the ceramic-containing web is formed to include a plurality of shield-cooling holes that provide the fluid communication between the first plenum and the cooling channel.
4. The turbine vane of claim 2 , wherein the ceramic-containing web is formed to include a second plenum that extends across at least a portion of the distance from the inner platform to the outer platform and the second plenum is spaced apart from the first plenum.
5. The turbine vane of claim 4 , wherein the ceramic-containing web is formed to include a plurality of shield-cooling holes that provide fluid communication between the second plenum and the cooling channel.
6. The turbine vane of claim 4 , wherein the ceramic-containing web is formed to include a plurality of web-cooling holes that provides fluid communication out of the second plenum along the pressure side of the airfoil.
7. The turbine vane of claim 4 , wherein the ceramic-containing web is formed to include at least one transfer aperture that provides fluid communication between the first plenum and the second plenum.
8. The turbine vane of claim 7 , wherein the ceramic-containing web is formed to include a plurality of web-cooling holes that provides fluid communication out of the second plenum along the pressure side of the airfoil.
9. The turbine vane of claim 4 , further comprising a restrictor plate arranged at an end of the first plenum and the second plenum, the restrictor plate formed to include a first restriction port in fluid communication with the first plenum and sized to cause a first pressure to be established within the first plenum by cooling air supplied to the first plenum that passes through the first restriction port, and the restrictor plate formed to include a second restriction port in fluid communication with the second plenum and sized to cause a second pressure to be established within the second plenum by cooling air supplied to the second plenum that passes through the second restriction port.
10. The turbine vane of claim 1 , wherein the metallic load shield is formed to include a plurality of discharge holes that provide fluid communication out of the cooling channel along the trailing edge of the airfoil.
11. A turbine vane for use in a gas turbine engine, the turbine vane comprising
an inner platform,
an outer platform spaced from the inner platform, and
an airfoil that extends from the inner platform to the outer platform, the airfoil including a ceramic-containing web that forms a pressure side of the airfoil and a metallic load shield that forms a suction side of the airfoil and extends from a leading edge of the airfoil to a trailing edge of the airfoil,
wherein the ceramic-containing web is formed to include a first plenum that extends at least a portion of the distance from the inner platform to the outer platform and the metallic load shield forms a plurality of discharge holes along the trailing edge of the airfoil in fluid communication with the first plenum to allow egress of cooling air in the plenum along the trailing edge of the airfoil.
12. The turbine vane of claim 11 , wherein a cooling channel is formed between the ceramic-containing web and the metallic load shield that provides fluid communication between the first plenum and the plurality of discharge holes.
13. The turbine vane of claim 12 , wherein the ceramic-containing web is formed to include a plurality of shield-cooling holes arranged to direct cooling air in the first plenum toward the metallic load shield and to provide fluid communication between the first plenum and the cooling channel.
14. The turbine vane of claim 12 , wherein the ceramic-containing web is formed to include a second plenum spaced apart from the first plenum.
15. The turbine vane of claim 14 , wherein the ceramic-containing web is formed to include a plurality of web-cooling holes that provide fluid communication out of the second plenum along the pressure side of the airfoil.
16. The turbine vane of claim 15 , wherein the ceramic-containing web is formed to include at least one transfer aperture that provides fluid communication between the first plenum and the second plenum.
17. The turbine vane of claim 15 , wherein the ceramic-containing web is formed to include a third plenum spaced apart from the first plenum and in fluid communication with the cooling channel.