Abstract: A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

Abstract: A blade outer air seal includes a carrier, a ceramic seal segment, and a face seal. The ceramic seal segment is supported on the carrier and has first and second axial ends, first and second circumferential sides, an inner side, and an outer side. The face seal is carried on the ceramic seal segment at the first axial end. The face seal has a radial seal wall and a tongue that extends axially from the radial seal wall.

Abstract: 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 carrier. At least two of the plurality of segments have a first wall and a second wall circumferentially spaced from one another and a base portion that extends from the first wall to the second wall. The base portion extends circumferentially outward past the first and second walls to form first and second sealing surfaces. An intersegment seal has a curved surface. The curved surface is engaged with the first and second sealing surfaces between the at least two segments.

Abstract: A blade outer air seal includes a carrier that has a dovetail and a ceramic seal segment supported on the dovetail. The ceramic seal segment has first and second axial ends, first and second circumferential sides, an inner side, an outer side, and first and second inward-facing dovetail hooks that project from the outer side and define a dovetail key. The ceramic seal segment is axially receivable onto the dovetail of the carrier via the dovetail key.

Abstract: A blade outer air seal assembly includes a carrier that has a slot and a hole that extends into the slot. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the carrier. At least one of the plurality of segments has a base portion and a first wall that extends axially and radially outwardly from the base portion. The first wall has an aperture. A pin extends through the hole and the aperture.

Abstract: A gas turbine engine includes a turbine section including at least one turbine rotor having at least one blade. A blade outer air seal is positioned radially outward of a radially outer tip of the at least one turbine blade. The blade outer air seal has a forward hook and an aft hook. The forward hook is supported on a forward retainer and the aft hook is supported on an aft hook retainer. The aft hook retainer provides structure to prevent rotation of the blade outer air seal relative to the aft hook retainer. There is an interference fit between the aft hook retainer and the forward retainer. A load path is provided from a static structure through the aft hook retainer to the forward retainer.

Abstract: An air seal assembly, comprising a control ring comprising a leading edge side and a trailing edge side opposite the leading edge side, a hook protruding axially from the trailing edge side, a clip receiver communicating through the control ring from the leading edge side to the trailing edge side, a clip mounting flange extending from the trailing edge side proximate the receiver; a blade outer air seal coupled to the control ring, the blade outer air seal comprises a body having a leading edge and a trailing edge opposite thereof, a pocket formed into the body having an upper region and a lower region, the pocket receives and engages with the hook; a notch is formed into the upper region, a shelf formed from the lower region extending axially outward from the pocket on the trailing edge side of the body; and a clip insertable into the clip receiver.

Abstract: A blade outer air seal includes a base portion that extends between a first circumferential side and a second circumferential side. A first wall is circumferentially spaced from a second wall. The first and second wall extend outward from the base portion and are connected by an outer wall to define a passage that extends in a generally axial direction along the base portion.

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks. The forward and aft hooks support the blade outer air seal. The blade outer air seal is formed with a central web. The forward and aft hooks extending from the central web at a T-joint. There is a pair of mating inner laminate at the T-joint each having an axially extending portion and a vertically extending portion. The pair of mating inner laminates have an interwoven connection. A method is also disclosed.

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of seal segments arranged circumferentially about an axis and mounted in the support structure by a carrier. A coverplate is arranged between the carrier and at least one of the plurality of seal segments. The coverplate forms a first passage between the coverplate and the carrier and a second passage between the coverplate and the seal segment.

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The blade outer air seal has a lip at an axial end engaged with the support structure. A seal structure has a seal portion and a wear liner portion joined by a radially extending portion. The seal portion is radially outward of the lip and the wear liner is radially inward of the lip.

Abstract: A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A support structure is arranged circumferentially about the axis of rotation and has a plurality of attachment members that extend radially inwardly. A blade outer air seal has a plurality of segments mounted in the support structure. Each segment has a first wall circumferentially spaced from a second wall. The first and second walls are joined to a base portion and an outer wall to define a passage that extends axially along the segment.

Abstract: A gas turbine engine includes a turbine blade rotating about an axis of rotation defining an axial direction. A blade outer air seal is positioned radially outward of a radially outer tip of the turbine blade. The blade outer air seal has a forward support and an aft support. The forward support is supported on a forward hook from a blade outer air seal support. The aft support is supported on an aft hook from the blade outer air seal support. The blade outer air seal has a central web extending between the forward support and the aft support and radially outwardly of the turbine blade radially outer tip. A radially outer chamber is defined radially outwardly of the central web, and axially intermediate the forward support and the aft support. The radially outer chamber is divided into at least two separate subchambers maintained at two different pressures. A forward subchamber is at a higher pressure than an aft subchamber. A seal separator separates the forward and aft subchambers.

Abstract: A blade outer air seal includes a base portion. A first wall and a second wall extend from the base portion. The first wall is circumferentially spaced from the second wall. The first and second walls extend at an angle less than 90° from the base portion. The first and second walls extend towards one another.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the 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 recess is arranged in at least one of the first wall and the second wall. An intersegment seal is arranged between the at least two segments. The intersegment seal has a circumferentially extending portion and a radially extending tab. The radially extending tab extends into the recess to define at least two cavities within the recess.

Abstract: A blade outer air seal assembly includes a support structure arranged about an axis. At least one blade outer air seal segment is mounted in the support structure. A flow guide is arranged between the support structure and the at least one blade outer air seal segment defining a passage between the flow guide and the blade outer air seal segment. The passage extends in a generally axial direction.