| 摘要 |
The invention relates to a core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft, comprising a nozzle intended to be arranged about a gas generator of the jet engine, the nozzle comprising a plurality of external air intake apertures emerging in a convergence zone between cold and hot flows from the gas generator and in which lobes , movable between two positions, are mounted; a first position in which they block the apertures of the nozzle and a second position, different from the first, in which they unblock said apertures and extend radially into the nozzle in order to admit external air, the lobes having an azimuthal component in the same direction in order to give a swirling motion to the external air admitted into the convergence zone when the lobes are in the second position. |
