Abstract: A shroud assembly is provided for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction. The shroud assembly includes: a shroud segment extending substantially along the circumferential direction and including a shroud wall, the shroud wall defining a shroud attachment opening; a hanger assembly including a hanger wall defining a hanger attachment opening; and an attachment pin assembly including a first member defining an interference fit with the hanger wall through the hanger attachment opening and including a shoulder contacting the hanger wall, the first member further extending through the shroud attachment opening and defining a hollow core; and a second member extending through the hollow core of the first member, the second member extending between a first end and a second end, the second member including a rim at the first end and a secondary attachment member at the second end.

Abstract: A shroud assembly is provided for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction. The shroud assembly includes: a shroud segment extending substantially along the circumferential direction and including a shroud wall, the shroud wall defining a shroud attachment opening; a hanger assembly including a hanger wall defining a hanger attachment opening; and an attachment pin assembly including a first member defining an interference fit with the hanger wall through the hanger attachment opening and including a shoulder contacting the hanger wall, the first member further extending through the shroud attachment opening and defining a hollow core; and a second member extending through the hollow core of the first member, the second member extending between a first end and a second end, the second member including a rim at the first end and a secondary attachment member at the second end.

Abstract: A shroud assembly is provided for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction. The shroud assembly includes: a shroud segment extending substantially along the circumferential direction and including a shroud wall, the shroud wall defining a shroud attachment opening; a hanger assembly including a hanger wall defining a hanger attachment opening; and an attachment pin assembly including a first member defining an interference fit with the hanger wall through the hanger attachment opening and including a shoulder contacting the hanger wall, the first member further extending through the shroud attachment opening and defining a hollow core; and a second member extending through the hollow core of the first member, the second member extending between a first end and a second end, the second member including a rim at the first end and a secondary attachment member at the second end.

Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.

Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.

Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.