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 hook circumferentially spaced from a second hook. A base portion extends from the first hook to the second hook. The carrier has a cavity on a radially inner surface between the carrier and the base portion.
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 hook circumferentially spaced from a second hook, and a base portion extending from the first hook to the second hook; and
the carrier having a first circumferential side, a second circumferential side, and a radially inner surface, the first and second circumferential sides in engagement with the first and second hooks, and the radially inner surface defining a cavity between the carrier and the base portion, wherein an impingement plate is arranged between the carrier and the base portion and the impingement plate wraps around a portion of the carrier.
2. The blade outer air seal assembly of claim 1 , wherein the cavity extends at least 50% of a circumferential width of the base portion.
3. The blade outer air seal assembly of claim 1 , wherein a plurality of grooves are arranged in the cavity.
4. The blade outer air seal assembly of claim 1 , wherein the impingement plate has a plurality of orifices.
5. The blade outer air seal assembly of claim 4 , wherein the plurality of orifices are configured to communicate cooling air to the at least one segment.
6. The blade outer air seal assembly of claim 1 , wherein a coating is on a surface between the carrier and the impingement plate.
7. The blade outer air seal assembly of claim 1 , wherein the impingement plate is a metallic material.
8. The blade outer air seal assembly of claim 1 , wherein the impingement plate is welded to the carrier.
9. The blade outer air seal of claim 1 , wherein an inlet hole extends through the carrier into the cavity.
10. The blade outer air seal of claim 8 , wherein the cavity has a lower pressure than a supply pressure.
11. The blade outer air seal assembly of claim 1 , wherein the carrier is a metallic material.
12. The blade outer air seal assembly of claim 1 , wherein the at least one segment is a ceramic matrix composite material.
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 an axis and mounted in a support structure via a carrier, at least one of the segments having a first hook circumferentially spaced from a second hook, and a base portion extending from the first hook to the second hook; and
the carrier having a first angled surface and a second angled surface on opposite sides of a radially inner surface, the first and second angled surfaces in engagement with the first and second hooks, the radially inner surface defining a cavity between the carrier and the base portion, wherein an impingement plate is arranged between the carrier and the base portion and the impingement plate wraps around a portion of the carrier.
14. The gas turbine engine of claim 13 , wherein a plurality of grooves are arranged in the cavity.
15. The gas turbine engine of claim 13 , wherein a plurality of holes having a diffusor are arranged in the cavity.
16. The gas turbine engine of claim 13 , wherein the impingement plate has a plurality of orifices configured to communicate cooling air to the at least one segment.