Bleed system for a turbofan with simplified control

摘要

The double flow turbojet comprises an intermediate structural casing (9) between the primary (2) and secondary (3) ducts which is located axially between low pressure (5) and high pressure (7) compressors. Discharge means allowing diversion of a part of the gas flow delivered by the low pressure compressor to the secondary duct comprise an annular cavity (16) forming a manifold located upstream of the intermediate casing in the external wall of the primary duct. Several axial conduits (18) in the intermediate casing and connected to the manifold are in permanent communication with the primary duct. Several tubes (20), located around the high pressure compressor, fitted with flow regulation valves (22) put the axial conduits in communication with the secondary duct.