Patent ID: 11879411
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A gas turbine engine defining an axial direction and a radial direction extending perpendicular from the axial direction, the gas turbine engine comprising:
a casing;
a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, wherein the forward rotor portion and the aft rotor portion are within a compressor of the gas turbine engine; and
a cooling system comprising:
a forward cooling fluid supply;
a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity for urging a flow of forward cooling fluid through the forward rotor cavity;
an aft cooling fluid supply;
an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity for urging a flow of aft cooling fluid through the aft rotor cavity; and
a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating the flow of forward cooling fluid and the flow of aft cooling fluid.