CPC F01D 11/18 (2013.01) [F01D 9/04 (2013.01); F01D 11/24 (2013.01); F01D 25/24 (2013.01); F01D 25/246 (2013.01); F05D 2220/32 (2013.01); F05D 2260/201 (2013.01)] | 20 Claims |
1. 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 are positioned radially outward from the outer casing wall and radially inward from the body of the thermal control ring.
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