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 includes 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 an outer wall. A rib extends from the base portion to the outer wall and spaced axially between the first and second walls.

Abstract: A gas turbine engine includes a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is positioned radially outwardly of the radially outer tip of the turbine blade. The blade outer air seal has a forward hook at an axially forward location and an aft hook at an axially aft location. An axial direction is defined by a rotational axis of the turbine blade. The blade outer air seal has a central web extending axially between the forward and aft hooks. The forward and aft hooks extend generally radially outward from the central web, and have slots for being received on forward and aft support hooks of a blade outer air seal support.

Abstract: A blade outer air seal includes a base portion. A first wall and a second wall extend radially from the base portion. The first wall is axially spaced from the second wall. The first and second walls extend in a circumferential direction. A first hook extends from the first wall and a second hook extends from the second wall. The first and second hooks extend in an axial direction towards one another to form a passage that extends in the circumferential direction. The passage is configured to receive a carrier. A tab extends radially outward from the second hook. The tab is configured to engage with the carrier.

Abstract: A blade outer air seal retention assembly may comprise a forward retention ring and an aft retention ring coupled to the forward retention ring. The forward retention ring may comprise a first shiplap flange extending aft from the forward retention ring. The aft retention ring may comprise a second shiplap flange extending forward from the aft retention ring.

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

Abstract: A blade outer air seal includes 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. The second wall has at least one wall window configured to engage with a support structure. An outer wall radially spaced from the base portion between the first and second walls. The outer wall has at least one outer wall window configured to engage with the support structure.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a support mountable to an engine static structure. The support has a main body extending axially between leading and trailing edge portions and circumferentially between opposed mate faces, and the main body includes a pair of opposed retention hooks extending inwardly from the leading and trailing edge portions to bound an elongated groove extending circumferentially between the opposed mate faces. A seal has a sealing portion that extends from an engagement portion. The sealing portion has a sealing face that extends circumferentially between first and second mate faces. An overwrap has one or more plies that follow a perimeter of the engagement portion to define an interface between the retention hooks and the engagement portion. A method of sealing is also disclosed.

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 via a carrier. At least one of the plurality of 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 hook extends from the base portion near the first axial side and faces towards the second axial side. A second hook extends from the base portion near the second axial side and faces towards the first axial side. A slot is in the second hook configured to receive a pin.

Abstract: An attachment body for a blade outer air seal includes a leading edge connected to a trialing edge by a radially inner wall and a radially outer wall. At least one forward hook extends from the radially outer wall. At least one aft hook extends from the radially outer wall. At least one post extends from the radially outer surface and has a blade outer air seal (BOAS) guide surface.

Abstract: A blade outer air seal assembly includes a seal segment that 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 an outer wall to define a circumferentially extending seal passage. A carrier has a platform. A portion of the platform is within the seal passage. A radially extending first hook protrudes from the platform and is configured to engage with a support structure.

Abstract: A clip for an air seal assembly, comprising a clip base having a control ring interface; a biasing element coupled to the clip base opposite the control ring interface; wherein the clip is insertable into a clip receiver and configured to engage a notch of a blade outer air seal and configured to detachably couple with a clip mounting flange.

Abstract: A blade outer air seal includes 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 hook extends from the base portion and circumferentially spaced from a second hook. The first and second hooks extend along an axial length of the base portion. The first circumferential side has a protrusion and the second circumferential side has a groove.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body extending circumferentially between opposed mate faces, the seal body having a seal face that bounds a gas path and an opposed impingement face, a seal carrier extending along the impingement face, and a seal member trapped between the seal carrier and the impingement face such that the seal member is circumferentially aligned with one of the mate faces. A method of sealing is also disclosed.

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.

Abstract: A gas turbine engine turbine section includes at least one blade extending radially outwardly to an outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip. The blade outer air seal has forward and aft hooks. The forward and aft hooks are supported on forward and aft seal hooks of an attachment block. The attachment block has a forward case mount hook and an aft case mount hook. The attachment block is supported on a forward case hook and an aft case hook of a static casing within the engine. The forward case mount hook and the aft case mount hook on the attachment block face in a common axial direction. The forward case hook and the aft case hook face in a common axial direction which is opposed to the common axial direction. A method is also disclosed.

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a central chamber within the attachment block, and communicates with cooling holes through a radially inner face of the attachment block to direct cooling air at the central web of the blade outer air seal. A blade outer air seal is also disclosed.

Abstract: A blade outer air seal includes a base portion. A first wall and a second wall extend radially from the base portion. The first wall is axially spaced from the second wall. The first and second walls extend in a circumferential direction. A first hook extends from the first wall and a second hook extends from the second wall. The first and second hooks extend in an axial direction towards one another to form a passage that extends in the circumferential direction. The passage is configured to receive a carrier. A tab extends radially outward from the second hook. The tab is configured to engage with the carrier.