Aircraft turbine engine comprising a discharge device

An aircraft turbine engine, comprising at least one first compressor, an annular combustion chamber and at least one first turbine, which define a first flow duct for a primary flow, wherein said aircraft turbine engine comprises, between said combustion chamber and said first turbine, a discharge device for discharging at least part of said primary flow, said discharge device comprising at least one valve or an annular row of valves, the or each valve comprising at least one scooping gate which is movable between a first position, in which said scooping gate has no influence on the supply of primary flow to said first turbine, and a second position, in which said scooping gate diverts at least part of the primary flow, which then does not supply the first turbine, radially towards the outside with respect to a longitudinal axis of the turbine engine,

• wherein the discharge device comprises a means for locking/unlocking the or each gate, a means for controlling said locking/unlocking means, and a means for assisting the opening of the gate.