Double box boas and carrier system
A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of seal segments that extend circumferentially about an axis and mounted in the support structure via a carrier. The carrier has a plurality of carrier segments that extend circumferentially about the axis. At least one of the seal segments have a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall axially spaced from a second wall. The first and second walls extend from the base portion to a first outer portion to form a first passage. The first wall has at least one slot engaged with a first carrier hook on one of the plurality of carrier segments. At least one of the carrier segments have a carrier window engaged with a support structure hook on the support structure.
1. A blade outer air seal assembly, comprising:
a support structure;
a blade outer air seal having a plurality of seal segments extending circumferentially about an axis and mounted in the support structure via a carrier, the carrier having a plurality of carrier segments extending circumferentially about the axis;
at least one of the seal segments having a base portion extending between a first circumferential side and a second circumferential side and from a first axial side to a second axial side, a first wall axially spaced from a second wall, the first and second walls extending from the base portion to a first outer portion to form a first passage, the first wall having at least one slot engaged with a first carrier hook on one of the plurality of carrier segments; and
at least one of the carrier segments having a carrier window engaged with a support structure hook on the support structure.
2. The blade outer air seal assembly of claim 1 , wherein the first carrier hook extends into the first passage.
3. The blade outer air seal assembly of claim 1 , wherein the first carrier hook extends axially aft.
4. The blade outer air seal assembly of claim 1 , wherein the at least one seal segment has a third wall and a fourth wall, the third and fourth walls joined by a second outer wall to form a second passage.
5. The blade outer air seal assembly of claim 4 , wherein a second carrier hook is engaged with a second slot in the third wall.
6. The blade outer air seal assembly of claim 5 , wherein the first carrier hook extends into the first passage and the second carrier hook extends into the second passage.
7. The blade outer air seal assembly of claim 1 , wherein the carrier window has a generally rectangular portion with notched corners.
8. The blade outer air seal assembly of claim 1 , wherein a second carrier window is spaced circumferentially from the carrier window.
9. The blade outer air seal assembly of claim 8 , wherein the carrier window and the second carrier window have the same shape.
10. The blade outer air seal assembly of claim 1 , wherein a circumferential width of the at least one slot is about 30% to 50% of a circumferential width of the at least one seal segment.
11. The blade outer air seal assembly of claim 1 , wherein a wedge seal is arranged between at least two of the seal segments.
12. The blade outer air seal assembly of claim 11 , wherein the base portion has a slanted portion at the first and second circumferential sides, the slanted portion configured to abut the wedge seal.
13. The blade outer air seal assembly of claim 1 , wherein the at least one carrier segment comprises a metallic material.
14. The blade outer air seal assembly of claim 1 , wherein the blade outer air seal comprises a ceramic matrix composite material.
15. A gas turbine engine, comprising:
a compressor section, a combustor section, and a turbine section arranged about an axis of rotation, the turbine section having a row of blades aft of a row of vanes;
a blade outer air seal assembly having a plurality of seal segments arranged radially outward of the row of blades and extending circumferentially about an axis, the plurality of segments mounted in a support structure via a carrier, the carrier having a plurality of carrier segments extending circumferentially about the axis;
at least one of the seal segments having a base portion extending between a first circumferential side and a second circumferential side and from a first axial side to a second axial side, a first wall axially spaced from a second wall, the first and second walls extending from the base portion to a first outer portion to form a first passage, the first wall having at least one slot engaged with a first carrier hook on one of the plurality of carrier segments; and
at least one of the carrier segments having a carrier window engaged with a support structure hook on the support structure.
16. The gas turbine engine of claim 15 , wherein the carrier supports a portion of a vane of the row of vanes.
17. The gas turbine engine of claim 15 , wherein the at least one of the seal segments has a third wall and a fourth wall, the third and fourth walls joined by a second outer wall to form a second passage, the first carrier hook extends into the first passage and a second carrier hook extends into the second passage.
18. The gas turbine engine of claim 15 , wherein the at least one of the seal segments comprises a ceramic matrix composite material.