Patent ID: 11920500
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 8:
9. A method of providing an air flow in a gas turbine engine, the gas turbine engine defining an axial centerline, the method comprising:
providing the air flow to an inducer assembly, the inducer assembly comprising:
a first ring with a first coefficient of thermal expansion; and
a second ring disposed coaxially with the first ring, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion of the first ring,
wherein a flow passage is defined at least in part between the first ring and the second ring, wherein the flow passage comprises a flow area between the first ring and the second ring, and wherein the flow passage defines a helical shape;

transferring thermal energy between the air flow and the first ring, between the air flow and the second ring, or both to change a size of the first ring relative to a size of the second ring and passively modulate an amount of the air flow through the flow passage; and
directing, with the inducer assembly, the air flow along an axial direction of the gas turbine engine, wherein the second ring is disposed inside of the first ring.