Patent ID: 11970946
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 6:
7. A gas turbine engine defining an axial direction and a radial direction, the engine comprising:
a compressor section;
a combustion section located downstream of the compressor section; and
a turbine section located downstream of the combustion section, wherein the turbine section includes a stage of rotor blades, a shroud hanger, and a clearance control assembly, the clearance control assembly comprising:
a case defining a first flange and a second flange extending radially outwardly along the radial direction, wherein the first flange defines a forward wall face and an aft wall face, and the second flange defines a forward wall face and an aft wall face, wherein the case is positioned outward along the radial direction from the stage of rotor blades, the case engaged with the shroud hanger at a first location; and
a baffle, wherein the baffle extends from the forward wall face of the first flange to the aft wall face of the second flange positioned outward from the case,, wherein the baffle, the case, the aft wall face of the first flange, and the forward wall face of the second flange form a chamber therebetween, the baffle having a forward end and an aft end, wherein the forward end of the baffle is engaged with the forward wall face of the first flange to form a first seal, wherein the aft end of the baffle is engaged with the aft wall face of the second flange to form a second seal,, wherein the baffle or the case defines an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.