Patent ID: 7810335
Filing Date: 2010-10-12
Classification: F02K,F05D,Y02T

Abstract:
1. A core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft, comprising a substantially cylindrical nozzle centered on a longitudinal axis (X-X) of the jet engine and intended to be arranged concentrically about a gas generator of the jet engine, the nozzle comprising a plurality of external air intake apertures distributed over its entire circumference, emerging in a convergence zone between the cold and hot flows from the gas generator and in which lobes, movable between two positions, are mounted; a first position in which the lobes block the apertures of the nozzle and a second position, different from the first, in which the lobes unblock said apertures and extend radially into the nozzle in order to admit air, external to the jet engine, into said convergence zone, wherein the lobes have an azimuthal component in the same direction such that each lobe is curved with a downstream end deviating from a radial pivoting plane of the lobe, in order to give a swirling motion to the external air admitted into the convergence zone when the lobes are in the second position.