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

Claim 16:
17. A cooling system for a gas turbine engine, the gas turbine engine comprising a casing and 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, wherein the forward rotor portion and the aft rotor portion are within a compressor of the gas turbine engine, the aft rotor cavity being fluidly isolated from the forward rotor cavity, the 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.