Patent ID: 9316111
Filing Date: 2016-04-19
CPC Classification: F01D

Claim Text:
1. An active tip clearance control (ATCC) system of a gas turbine engine comprising an ATCC manifold disposed adjacent a rotor case, the manifold configured for directing air over the rotor case, an inlet passage fluidly connecting the ATCC manifold with an air source selected from one of ambient air and a fan driven bypass air flow directed through a bypass duct of the engine, a vent passage in fluid communication with the manifold and the atmosphere for venting air received from the ATCC manifold to the atmosphere, a controllable valve receiving and controlling a compressor air flow, and an ejector for ejecting the controlled compressor air flow to selectively drive only said selected one of ambient air and fan driven bypass air flow through the ATCC manifold.