BACKGROUND

This application relates to a blade outer air seal assembly.

Gas turbine engines are known and typically include a compressor compressing air and delivering it into a combustor. The air is mixed with fuel in the combustor and ignited. Products of the combustion pass downstream over turbine rotors, driving them to rotate.

It is desirable to ensure that the bulk of the products of combustion pass over turbine blades on the turbine rotor. As such, it is known to provide blade outer air seals radially outwardly of the blades. Blade outer air seals have been proposed made of ceramic matrix composite fiber layers.

SUMMARY OF THE INVENTION

In one exemplary embodiment, 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.

In a further embodiment of the above, the first carrier hook extends into the first passage.

In a further embodiment of any of the above, the first carrier hook extends axially aft.

In a further embodiment of any of the above, the at least one seal segment has a third wall and a fourth wall. The third and fourth walls are joined by a second outer wall to form a second passage.

In a further embodiment of any of the above, a second carrier hook is engaged with a second slot in the third wall.

In a further embodiment of any of the above, the first carrier hook extends into the first passage and the second carrier hook extends into the second passage.

In a further embodiment of any of the above, the carrier window has a generally rectangular portion with notched corners.

In a further embodiment of any of the above, a second carrier window is spaced circumferentially from the carrier window.

In a further embodiment of any of the above, the carrier window and the second carrier window have the same shape.

In a further embodiment of any of the above, 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.

In a further embodiment of any of the above, a wedge seal is arranged between at least two of the seal segments.

In a further embodiment of any of the above, the base portion has a slanted portion at the first and second circumferential sides. The slanted portion configured to abut the wedge seal.

In a further embodiment of any of the above, the at least one carrier segment is a metallic material.

In a further embodiment of any of the above, the at least one blade outer air seal is a ceramic matrix composite material.

In another exemplary embodiment, a gas turbine engine includes a compressor section, a combustor section, and a turbine section arranged about an axis of rotation. The turbine section has a row of blades aft of a row of vanes. A blade outer air seal assembly has a plurality of segments arranged radially outward of the row of blades and extend circumferentially about an axis. The plurality of segments are mounted in a 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 has 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 is 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 has a carrier window engaged with a support structure hook on the support structure.

In a further embodiment of any of the above, the carrier supports a portion of the vane.

In a further embodiment of any of the above, the at least one seal segment has a third wall and a fourth wall. The third and fourth walls are joined by a second outer wall to form a second passage. The first carrier hook extends into the first passage. A second carrier hook extends into the second passage.

In a further embodiment of any of the above, the at least one seal segment is a ceramic matrix composite material.

In another exemplary embodiment, a method of assembling a blade outer air seal assembly includes mounting a carrier segment to a support structure by inserting a support structure hook into a window on the carrier segment. The carrier segment is slid axially aft with respect to the support structure such that the support structure hook contacts a surface of the carrier segment. A blade outer air seal segment having a first passage and a second passage is mounted onto the carrier segment by inserting a first carrier hook into the first passage and a second carrier hook into the second passage.

In a further embodiment of any of the above, the blade outer air seal segment is a ceramic matrix composite material and the carrier segment is a metallic material.

