Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a mount assembly. The carrier segment includes an outer wall, a first flange that extends radially inward from the outer wall, and a second flange axially spaced apart from the first flange and extending radially inward from the outer wall. The blade track segment includes a shroud wall and an attachment feature that extends radially outward from the shroud wall. The mount assembly includes a pin that extends axially into the second flange, through the attachment feature, and into the first flange so as to couple the blade track segment to the carrier segment and a pin retention plug that is press fit into the second flange axially aft of the pin to block removal of the pin through the second flange.

Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a buffer air seal assembly. The carrier segment includes a cantilevered wall extending radially inwardly within a recess so as to form a groove between the cantilevered wall and the inner wall of the recess. The carrier segment includes a second recess located at an end of the groove that opens deeper into the segment than the groove. The buffer air seal assembly includes first and second seal members arranged in the groove, the second seal member being arranged radially outward of the first seal member. A first end of the second seal member extends circumferentially beyond the first circumferential end of the first groove, and the first end of the second seal member extends radially outwardly into the second recess so as to block circumferential movement of the second seal member.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system is arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a buffer air seal assembly. The carrier segment includes a cantilevered wall extending radially inwardly within a recess so as to form a groove between the cantilevered wall and the inner wall of the recess. The buffer air seal assembly includes first, second, and third seal members arranged in the groove. The second and third seal members are aligned with each other and arranged radially outward of the first seal member. The cantilevered wall a barrier portion wider than a main portion of the wall such that the barrier portion extends at least partially into the groove. The second and third seal members are arranged on opposing circumferential sides of the barrier portion such that the barrier portion blocks circumferential movement of the second and third seal members.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes a body segment and a damping segment that extends along a curvilinear path.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

Abstract: An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a pin. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The pin couples the blade track segment to the carrier segment. The carrier segment may include cooling passageways to conduct cooling air to preselected cooling areas located on the blade track segment.

Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a buffer air seal assembly. The carrier segment includes a cantilevered wall extending radially inwardly within a recess so as to form a groove between the cantilevered wall and the inner wall of the recess. The carrier segment includes a second recess located at an end of the groove that opens deeper into the segment than the groove. The buffer air seal assembly includes first and second seal members arranged in the groove, the second seal member being arranged radially outward of the first seal member. A first end of the second seal member extends circumferentially beyond the first circumferential end of the first groove, and the first end of the second seal member extends radially outwardly into the second recess so as to block circumferential movement of the second seal member.

Abstract: An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a pin. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The pin couples the blade track segment to the carrier segment. The carrier segment may include cooling passageways to conduct cooling air to preselected cooling areas located on the blade track segment.

Abstract: A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system is arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

Abstract: A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a blade track segment arranged circumferentially at least partway around an axis of the gas turbine engine, a carrier segment arranged circumferentially at least partway around the axis, and a mount assembly configured to couple the blade track segment to the carrier segment. The turbine vane is located axially aft of the turbine shroud assembly and helps retain the mount assembly in place.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

Abstract: A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.

Abstract: A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a carrier segment arranged circumferentially at least partway around an axis and a blade track segment supported by the carrier segment to locate the blade track segment radially outward of the axis. The turbine vane is located axially forward of the turbine shroud assembly and cooperates with the turbine shroud assembly to form a tortuous flow path therebetween.

Abstract: A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

Abstract: A turbine vane assembly includes a flow path ring, an airfoil heat shield, and a seal. The flow path ring is made of ceramic matrix composite materials. The airfoil heat shield is made of ceramic matrix composite materials. The seal resists passage of gases through a gap formed between the flow path ring and the airfoil heat shield along an interface at the airfoil aperture.