CMC BOAS arrangement
A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure via a carrier. At least one of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. The first and second walls extend at an angle less than 90° from the base portion. The carrier has a flat portion that extends from the first wall to the second wall.
1. A blade outer air seal assembly, comprising:
a blade outer air seal having a plurality of segments extending circumferentially about an axis and mounted in a support structure via a carrier, at least one of the segments having a first wall circumferentially spaced from a second wall, a base portion extending from the first wall to the second wall, the first and second walls extending at an angle less than 90° from the base portion; and
the carrier having a flat portion extending from the first wall to the second wall, wherein the carrier has a first angled surface and a second angled surface, the first and second angled surfaces in engagement with the first and second walls.
2. The blade outer air seal assembly of claim 1 , wherein an aft wall extends circumferentially outward past the first and second angled surfaces at an aft end of the carrier.
3. The blade outer air seal assembly of claim 1 , wherein a first hook extends from the first wall and a second hook extends from the second wall.
4. The blade outer air seal assembly of claim 3 , wherein the first and second hooks extend away from one another.
5. The blade outer air seal assembly of claim 1 , wherein a plurality of holes extend through the flat portion.
6. The blade outer air seal assembly of claim 1 , wherein the first and second walls are engaged with a wedge seal.
7. The blade outer air seal assembly of claim 1 , wherein the carrier is a metallic material.
8. The blade outer air seal assembly of claim 1 , wherein the at least one segment is a ceramic matrix composite material.
9. The blade outer air seal assembly of claim 1 , wherein the carrier includes a carrier hook extending radially outward and engaging the support structure, and the carrier hook extends across a circumferential width of the carrier.
10. A blade outer air seal assembly, comprising:
a blade outer air seal having a plurality of segments extending circumferentially about an axis and mounted in a support structure via a carrier, at least one of the segments having a first wall circumferentially spaced from a second wall, a base portion extending from the first wall to the second wall, the first and second walls extending at an angle less than 90° from the base portion; and
the carrier having a flat portion extending from the first wall to the second wall, wherein the carrier includes a carrier hook extending radially outward and engaging the support structure.
11. The blade outer air seal assembly of claim 10 , wherein the carrier hook extends across a circumferential width of the carrier.
12. The blade outer air seal assembly of claim 10 , wherein a first hook extends from the first wall and a second hook extends from the second wall, the first and second hooks extending away from one another.
13. A gas turbine engine, comprising:
a compressor section, a combustor section, and a turbine section arranged about an axis of rotation;
a blade outer air seal having a plurality of segments extending circumferentially about the axis of rotation and mounted in a support structure via a carrier, at least one of the segments having a first wall circumferentially spaced from a second wall, a base portion extending from the first wall to the second wall, the first and second walls extending at an angle less than 90° from the base portion; and
the carrier having a flat portion extending from the first wall to the second wall, wherein the carrier has a first angled surface and a second angled surface, the first and second angled surfaces in engagement with the first and second walls.
14. The gas turbine engine of claim 13 , a wherein an aft wall extends circumferentially outward past the first and second angled surfaces at an aft end of the carrier.
15. The gas turbine engine of claim 13 , wherein a first hook extends from the first wall and a second hook extends from the second wall, the first and second hooks extend away from one another.
16. The gas turbine engine of claim 13 , wherein the carrier includes a carrier hook extending radially outward and engaging the support structure.
17. The gas turbine engine of claim 16 , wherein the carrier hook extends across a circumferential width of the carrier.
18. The gas turbine engine of claim 13 , wherein a plurality of holes extend through the flat portion.
19. The gas turbine engine of claim 13 , wherein the first and second walls are engaged with a wedge seal.
20. The gas turbine engine of claim 13 , wherein the carrier is a metallic material and the at least one segment is a ceramic matrix composite material.