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;

• anda turbine section, wherein the turbine section includes a vane stage and a rotor stage, wherein the rotor stage comprises a bladed rotor and an annular shroud having a circumference;wherein the vane stage is disposed forward of and adjacent the rotor stage, and the annular shroud is independent of the vane stage;
• andwherein the bladed rotor includes a disk and a plurality of rotor blades extending radially outward from the disk, wherein each rotor blade has a leading edge and a blade tip surface;
• andwherein the annular shroud is disposed radially outside of the bladed rotor and comprises a primary segment (PS) and a forward segment (FS), and the primary segment and the forward segment extend around the entire circumference of the annular shroud;
• andwherein the primary segment has a PS forward end surface and a PS inner radial surface;
• wherein the forward segment is disposed forward of the rotor blades and is configured to deflect core gas flow away from a blade tip gap disposed between the PS inner radial surface and the blade tip surface of each said rotor blade of the plurality of rotor blades;
• and wherein the forward segment has an FS inner radial surface that extends between an FS forward end surface and an FS aft end surface.