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. At least two 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. A first hook extends from the first wall and a second hook extends from the second wall. A wedge seal is arranged between the at least two adjacent seal segments. A clip is configured to bias the wedge seal radially inward.
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, at least two of the segments having a first wall circumferentially spaced from a second wall, and a base portion extending from the first wall to the second wall, a first hook extending from the first wall and a second hook extending from the second wall;
a wedge seal arranged between the at least two adjacent seal segments; and
a clip configured to bias the wedge seal radially inward the clip having a first axially extending portion and a second axially extending portion spaced radially from the first axially extending portion by a radially extending portion.
2. The blade outer air seal assembly of claim 1 , wherein the wedge seal extends at least 80% of an axial length of the at least two adjacent seal segments.
3. The blade outer air seal assembly of claim 1 , wherein the wedge seal has a generally triangular cross section.
4. The blade outer air seal assembly of claim 1 , wherein the wedge seal has a first angled surface and a second angled surface, the first and second angled surfaces configured to mate with the first and second walls on the at least two adjacent seal segments.
5. The blade outer air seal assembly of claim 1 , wherein the radially extending portion is arranged near a forward end of the at least two adjacent seal segments.
6. The blade outer air seal assembly of claim 1 , wherein the clip engages the at least two seal segments between the first and second axially extending portions.
7. The blade outer air seal assembly of claim 1 , wherein at least one of the first and second axially extending portions is curved to provide a spring force.
8. The blade outer air seal assembly of claim 7 , wherein the at least one of the first and second axially extending portions that is curved contacts the at least two adjacent seal segments at two points spaced in the axial direction.
9. The blade outer air seal assembly of claim 1 , wherein a gap is defined between the at least two adjacent seal segments, and the gap permits air to flow radially outward into the gap.
10. The blade outer air seal assembly of claim 1 , wherein the at least two segments are a ceramic matrix composite material.
11. The blade outer air seal assembly of claim 1 , wherein the wedge seal is a ceramic matrix composite material.
12. The blade outer air seal assembly of claim 1 , wherein the wedge seal is a metallic material.
13. The blade outer air seal assembly of claim 1 , wherein the clip is a metallic material.
14. 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, at least two of the segments having a first wall circumferentially spaced from a second wall, and a base portion extending from the first wall to the second wall, a first hook extending from the first wall and a second hook extending from the second wall;
a wedge seal arranged between the at least two adjacent seal segments;
a clip configured to bias the wedge seal radially inward; and
a gap is defined between the at least two adjacent seal segments, and the gap permits air to flow radially outward into the gap, wherein the wedge seal includes channels extending radially inwardly from the gap.
15. The blade outer air seal assembly of claim 14 , wherein the wedge seal is a ceramic matrix composite material.
16. 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, at least two of the segments having a first wall circumferentially spaced from a second wall, and a base portion extending from the first wall to the second wall, a first hook extending from the first wall and a second hook extending from the second wall;
a wedge seal arranged between the at least two adjacent seal segments; and
a clip configured to bias the wedge seal radially inward, the clip having a first axially extending portion and a second axially extending portion spaced radially from the first axially extending portion by a radially extending portion.
17. The gas turbine engine of claim 16 , wherein the wedge seal has a first angled surface and a second angled surface, the first and second angled surfaces configured to mate with the first and second walls on the at least two adjacent seal segments.
18. The gas turbine engine of claim 16 , wherein the clip engages the at least two seal segments between the first and second axially extending portions.
19. The gas turbine engine of claim 16 , wherein a gap is defined between the at least two adjacent seal segments, and the gap permits air to flow radially outward into the gap.
20. The gas turbine engine of claim 19 , wherein the wedge seal includes channels extending radially inwardly from the gap.