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

Claim 0:
1. A clearance control assembly for a gas turbine engine, the gas turbine engine defining an axial direction and a radial direction and including a stage of rotor blades and a shroud hanger, the 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 configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine, the case further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine; 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 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 define 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, and 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, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.