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 blade outer air seal has a plurality of segments arranged circumferentially about the axis of rotation and mounted in a support structure radially outward of the outer tip. Each of the segments have a radially inner surface and a radially outer surface and four hooks protruding radially outward from the radially outer surface and extending along the segment in an axial direction.

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 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. 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: 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 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 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 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 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: 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 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 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 blade outer air seal has a plurality of segments arranged circumferentially about the axis of rotation and mounted in a support structure radially outward of the outer tip. Each of the segments have a radially inner surface and a radially outer surface and four hooks protruding radially outward from the radially outer surface and extending along the segment in an axial direction.

Abstract: A method of fabricating a package for a micro-electromechanical systems (MEMS) device. A flex circuit interconnect subassembly for the package is made by placing a flex circuit on a pad insert, attaching a carrier insert to the pad insert to deflect the lead portions of the flex circuit, and applying a cover insert to the pad insert, after the attachment of the carrier insert, to re-deflect the lead portions of the flex circuit toward the device bond sites. The flex circuit interconnect subassembly may be combined with an electronic device die/carrier subassembly to form a completed electronic device package. The flex circuit interconnect subassembly and the die/carrier subassembly are joined using mechanical interlocking layers. The invention is particularly suited for making such an electronic device die/carrier subassembly which has a MEMS die permanently affixed to a carrier.