Gas turbine engine with a rotor stage shroud

A gas turbine engine having an axial centerline, the gas turbine engine comprising:

• a compressor section;
• a combustor section;
• and
• a turbine section, wherein the turbine section includes a rotor stage and an annular shroud assembly, wherein the rotor stage includes a bladed rotor;
• wherein the annular shroud assembly is disposed radially outside of the bladed rotor, and extends circumferentially around the bladed rotor, and is coupled with a turbine support case, wherein the annular shroud assembly comprises:
• a shroud comprising a plurality of shroud segments that collectively form the shroud, wherein each shroud segment includes a ring portion, a forward leg, and an aft leg;
• a shroud segment housing;
• a cover;
• and
• a plurality of shroud pins disposed to connect the shroud to the shroud segment housing and the cover;
• wherein the shroud segment housing and the turbine support case are engaged with one another and are configured to permit relative movement therebetween;
• and
• wherein the annular shroud assembly and the turbine support case are configured to permit radial movement between the annular shroud assembly and the entirety of the turbine support case.