CMC vane with rotatable baffle design to accommodate re-stagger
A method of forming a vane assembly for a gas turbine engine includes the steps of 1) determining a re-stagger angle for an airfoil on a ceramic matrix composite (“CMC”) vane, 2) determine an adjusted position of a baffle to be inserted within a central chamber in the vane, inserting the baffle into a bathtub seal, and adjusting an upper face of the baffle to an orientation relative to a bathtub seal support face to account for the adjusted position of the baffle and 3) fixing the baffle upper face to the bathtub seal flange support face. A vane assembly and a gas turbine engine are also disclosed.
1. A method of forming a vane assembly for a gas turbine engine comprising the steps of:
1) determining a re-stagger angle for an airfoil on a ceramic matrix composite (“CMC”) vane;
2) determine an adjusted position of a baffle to be inserted within a central chamber in the vane, inserting the baffle into a bathtub seal, and adjusting an upper face of the baffle to an orientation relative to a bathtub seal support face to account for the adjusted position of the baffle; and
3) fixing the baffle upper face to the bathtub seal flange support face, the baffle upper face is beyond the bathtub seal flange support face, with the baffle extending from the baffle upper face through the bathtub seal.
2. The method as set forth in claim 1 , wherein step 3) is performed by brazing.
3. The method as set forth in claim 1 , wherein the fixed bathtub seal and baffle are inserted into the central chamber in the vane and the vane is then mounted into a vane row with the bathtub seal providing support between the vane, the baffle and a static structure.
4. The method as set forth in claim 3 , wherein the static structure includes a first vane support having a tab extending into a seal chamber defined between an inner and an outer wall of the bathtub seal.
5. The method as set forth in claim 4 , wherein a mount structure on an upper surface of a vane platform is provided with a coating on an outer surface, and adjusting the coating to account for the re-stagger angle of the airfoil and connecting the mount structure on the vane to the bathtub seal.
6. The method as set forth in claim 5 , wherein the mount structure of the vane is connected to the bathtub seal through a flange cap secured across the outer wall of the bathtub seal and the mount structure.
7. The method as set forth in claim 3 , including the steps of assembling a vane row of a plurality of the vanes with at least a first vane having the airfoil with a first re-stagger angle that is different relative to at least the airfoil of a second of the plurality of vanes and the orientation of the baffle upper face relative to the bathtub seal support face is distinct between the first vane and the second vane.
8. A vane assembly comprising:
a vane having an outer platform with a mount structure and an airfoil extending inwardly from the mount structure 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 platform to an upper face fixed to a bathtub seal at a bathtub seal support face, and an orientation of said upper face relative to said bathtub seal support face being adjusted to accommodate a re-stagger angle on the airfoil of the vane;
the vane is mounted into a vane row with the bathtub seal providing support between the vane, the baffle and a static structure; and
wherein the static structure includes a first vane support having a tab extending into a seal chamber defined between an inner and an outer wall of the bathtub seal.
9. The vane assembly as set forth in claim 8 , wherein the upper face and the support face are brazed together.
10. The vane assembly as set forth in claim 8 , wherein a mount structure on an upper surface of a vane platform is provided with a coating on an outer surface.
11. The vane assembly as set forth in claim 10 , wherein a flange cap extends across the mount structure of the vane and across an outer wall of the bathtub seal.
12. The vane assembly as set forth in claim 8 , wherein a flange cap extends across the mount structure of the vane and across the outer wall of the bathtub seal.
13. The vane assembly as set forth in claim 8 , including a vane row of a plurality of the vanes with at least a first vane having the airfoil with a first re-stagger angle that is different relative to at least the airfoil of a second of the plurality of vanes and the orientation of the baffle upper face relative to the bathtub seal support face is distinct between the first vane and the second vane.
14. 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 vane rows including a vane assembly having a plurality of vanes with an outer platform having a mount structure and an airfoil extending inwardly from the mount structure and the vane formed of ceramic matrix composites (“CMC”), the vane having an internal cooling chamber; and
a metal baffle received within said internal cooling chamber and extending beyond said platform to an upper face fixed to a bathtub seal at a bathtub seal support face, and an orientation of said upper face relative to said bathtub seal support face being adjusted to accommodate a re-stagger angle on the airfoil of the vane; and
there being a plurality of re-stagger angles on the airfoils of the plurality of vanes, with an orientation of at least one of the metal baffle upper face relative to the bathtub seal support face being distinct from at least another of the metal baffle upper face.
15. The gas turbine engine as set forth in claim 14 , wherein the upper face and the support face are brazed together.
16. The gas turbine engine as set forth in claim 14 , wherein the vane is mounted into a vane row with the bathtub seal providing support between the vane and the baffle and static structure.
17. The gas turbine engine as set forth in claim 16 , wherein there are a plurality of the vanes including a first vane having an airfoil with a first re-stagger angle that is different relative to at least the airfoil of a second of the plurality of vanes and the orientation of the upper face relative to the bathtub seal support face is distinct between the first vane and the second vane.
18. The gas turbine engine as set forth in claim 14 , wherein there are a plurality of the vanes including a first vane having an airfoil with a first re-stagger angle that is different relative to at least the airfoil of a second of the plurality of vanes and the orientation of the upper face relative to the bathtub seal support face is distinct between the first vane and the second vane.
19. The method as set forth in claim 3 , wherein the vane row having a plurality of the vanes, with distinct re-stagger angles for at least some of the plurality of vanes, and an orientation of the bathtub upper face relative to the bathtub seal flange support face being distinct for ones of the plurality of vanes having distinct re-stagger angles.