Gas turbine engine with clearance control system

A gas turbine engine, wherein the gas turbine engine defines an axial direction, a centerline axis parallel to the axial direction, a radial direction extended from the centerline axis, and a circumferential direction relative to the centerline axis, the gas turbine engine comprising:

• a first turbine rotor assembly comprising a plurality of first turbine rotor blades extended within a gas flowpath;
• and
• a casing surrounding the first turbine rotor assembly, wherein the casing comprises
• an outer casing wall extended around the first turbine rotor assembly;
• a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly;
• and
• a thermal control ring positioned outward along the radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.