Bathtub seal for damping CMC vane platform
A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites (“CMC”). The vane having an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the outer platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal having an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a base wall define a bathtub seal chamber. The base wall is in contact with the outer platform. The vane is connected to the outer wall. The static structure is received within the bathtub seal chamber. A connection is configured to deliver pressurized air to the bathtub seal chamber. A gas turbine engine is also disclosed.
1. A vane assembly comprising:
a vane has an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites (“CMC”), the vane having an internal cooling chamber;
a metal baffle received within said internal cooling chamber and extending beyond said outer platform, a bathtub seal, having a central portion receiving said metal baffle, said metal baffle having a central chamber and cooling air holes to deliver cooling air into said internal cooling chamber, said metal baffle having an upper face, and said bathtub seal having an inner wall defining a riser and extending to a support face, said metal baffle upper face radially outward of bathtub seal support face, said bathtub seal having the inner wall and an outer wall spaced from each other and both outward of said central chamber of said metal baffle, and said inner wall, said outer wall and a base wall defining a bathtub seal chamber, said base wall in contact with said outer platform, a vane mount structure connected to said outer wall, and a vane support structure received within said bathtub seal chamber; and
a connection configured to deliver pressurized air to the bathtub seal chamber.
2. The vane assembly as set forth in claim 1 , wherein said base wall having a first surface area in contact with the outer platform, the outer platform having a second surface area, and the first surface area being at least 50% of the second surface area.
3. The vane assembly as set forth in claim 2 , wherein the first surface area is at least 75% of the second surface area.
4. The vane assembly as set form in claim 3 , wherein the upper face and the support face are brazed together.
5. The vane assembly as set forth in claim 3 , wherein the vane is mounted into a vane row with the bathtub seal providing support between the vane, the baffle and static structure.
6. The vane assembly as set forth in claim 3 , wherein the static structure includes a first vane support having a tab extending into the bathtub seal chamber.
7. The vane assembly as set form in claim 6 , wherein the upper face and the support face are brazed together.
8. The vane assembly as set form in claim 1 , wherein the upper face and the support face are brazed together.
9. The vane assembly as set forth in claim 1 , wherein the vane is mounted into a vane row with the bathtub seal providing support between the vane, the baffle and static structure.
10. The vane assembly as set forth in claim 9 , wherein the static structure includes a first vane support having a tab extending into the bathtub seal chamber.
11. A gas turbine engine comprising:
a compressor section, a combustor and a turbine section, the turbine section including rotating blade rows alternating with static vane rows, and the static vane rows including a vane assembly having a plurality of vanes with an outer platform having mount structure and an airfoil extending inwardly from the outer platform and the vane formed of ceramic matrix composites (“CMC”), the vane having an internal cooling chamber;
a metal baffle received within said internal cooling chamber and extending beyond said outer platform, a bathtub seal having a central portion receiving said metal baffle, said metal baffle having a central chamber and cooling air holes to deliver cooling air into said internal cooling chamber, said metal baffle having an upper face, and said bathtub seal having an inner wall defining a riser and extending to a support face, said metal baffle upper face radially outward of bathtub seal support face, said bathtub seal having the inner wall and an outer wall spaced from each other and both outward of said central chamber of said metal baffle, and said inner wall, said outer wall and a base wall defining a bathtub seal chamber, said bottom wall in contact with an upper surface of said outer platform, a vane mount structure connected to said outer wall, and a vane support structure received within said bathtub seal chamber; and
a connection to deliver pressurized into the bathtub seal chamber.
12. The gas turbine engine as set forth in claim 11 , wherein said base wall having a first surface area in contact with the outer platform, the outer platform having a second surface area, and the first surface area being at least 50% of the second surface area.
13. The gas turbine engine as set forth in claim 12 , wherein the first surface area is at least 75% of the second surface area.
14. The gas turbine engine as set form in claim 13 , wherein the upper face and the support face are brazed together.
15. The gas turbine engine as set forth in claim 13 , wherein the bathtub seal providing support between the vane, the baffle and static structure.
16. The gas turbine engine as set forth in claim 13 , wherein the static structure includes a first vane support having a tab extending into the bathtub seal chamber.
17. The gas turbine engine as set form in claim 16 , wherein the upper face and the support face are brazed together.
18. The gas turbine engine as set form in claim 11 , wherein the upper face and the support face are brazed together.
19. The gas turbine engine as set forth in claim 11 , wherein the bathtub seal providing support between the vane, the baffle and static structure.
20. The gas turbine engine as set forth in claim 19 , wherein the static structure includes a first vane support having a tab extending into the bathtub seal chamber.