AIR DISCHARGE SYSTEM FOR AN AERONAUTICAL TURBINE ENGINE COMPRESSOR

摘要

The invention relates to an air discharge system for an aeronautical turbine engine compressor, comprising: at least one discharge valve (10), each including a valve body capable of moving between an open position and a closed position for the discharge valve; a camshaft (22) comprising a cylindrical rod having a cam mounted so as to bear against the valve body such that the rotation of the camshaft causes the valve body to move between the open and closed positions thereof; and means for maintaining the cam such that it bears constantly against the valve body. The system also includes: at least one main electric engine (30), the rotor of which is capable of rotating the camshaft of each discharge valve; and an electronic control system (32) for each main electric engine.