Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a retainer. The carrier segment is formed to include an attachment-receiving space. The blade track segment includes a shroud wall and attachment flanges that extends radially outward from the shroud wall into the attachment-receiving space of the carrier segment. The retainer couples the blade track segment to the carrier segment.

Abstract: A turbine section of a gas turbine engine includes a case, a plurality of flow path components, and a mounting system. The case extends circumferentially at least partway around an axis of the gas turbine engine. The plurality of flow path components includes a flow path segment and a turbine vane. The mounting system couples the flow path segment to the case to support the flow path segment radially relative to the axis of the gas turbine engine.

Abstract: A turbine shroud assembly includes a carrier assembly, a blade track segment, a retainer, and a clip shim. The carrier assembly is arranged circumferentially at least partway around an axis. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the carrier assembly and the blade track segment. The clip shim is located between the carrier assembly and the blade track and configured to urge the blade track segment axially toward the carrier assembly.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Abstract: A turbine shroud assembly includes a carrier segment and a blade track segment. The carrier segment includes an outer wall, a first mount flange, and a second mount flange having a chordal seal. The blade track segment includes a shroud wall and an attachment feature. The mount assembly couples the blade track segment to the carrier segment.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount pin assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mount pin assembly is configured to couple the seal segment to the carrier.

Abstract: A turbine shroud assembly includes a carrier assembly, a blade track segment, and a retainer. The carrier assembly is arranged circumferentially at least partway around an axis and includes a fore carrier segment and an aft carrier segment coupled with the fore carrier. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the fore carrier segment, the blade track segment, and the aft carrier segment to couple the blade track segment with the carrier assembly.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Abstract: A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier.

Abstract: A combustor adapted for use in a gas turbine engine includes a combustor shell comprising metallic materials. The combustor shell is formed to define an internal space. The combustor further includes a heat shield mounted to an axially aft surface of the combustor shell within the internal space and a combustor liner arranged to extend along inner surfaces of the combustor shell within the internal space. The combustor liner cooperates with the heat shield to define a combustor chamber.

Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Abstract: A combustor for a gas turbine engine includes a combustor shell, a heat shield and a burner seal. The combustor shell includes metallic materials and is formed to define an interior combustion space. The heat shield includes ceramic matrix composite materials and is configured to shield a portion of the combustor shell from the interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield.