Turbojet engine thrust reverser and exhaust nozzle assembly

Abstract

An exhaust assembly for a jet powerplant of a supersonic airplane comprising a rear structure fitted with a thrust reverser. The rear structure includes a primary multi-flap nozzle of variable cross-section situated downstream of a primary duct, a secondary multi-flap nozzle of variable cross-section situated downstream of a secondary duct enclosing the primary duct and a fairing enclosing the secondary duct and fitted with a throat downstream of an exhaust orifice of the secondary nozzle, the throat being followed by a diverging portion. The thrust reverser comprises two eyelids affixed in a pivotable manner to the fairing, one on each side to of an axial plane of symmetry. The eyelids are movable between an active, thrust-reversal position wherein the eyelids project transversely into a gas jet downstream of the fairing to deflect the gas jet in a forward direction for thrust-reversal and an inactive, forward-thrust position wherein the eyelids are situated in an extension of the fairing. The two eyelids are each mounted on the fairing by two lateral linkrods which are freely pivotable relative to the fairing about a transverse axis in the vicinity of the axial plane of symmetry. The eyelids furthermore are retained on the fairing by two outer actuators and by two inner actuators. Only the latter will be driven in the forward-thrust mode. The external linear actuators are driven when passing into the thrust-reversal mode.