Patent attributes
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.
