Jet engine two dimensional, asymmetric afterburner nozzle

Abstract

An improved jet engine two dimensional, asymmetric afterburner nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its low profile configuration, simplicity of construction, and lack of interference with, or excessive intrusion into, the wing spar structural space within the airfoil; yet, which permits minimization of the included angle between the wing chord reference plane and the visual line-of-sight from the airfoil trailing edge into the jet engine nozzle while in its cruise position. More specifically, the present invention pertains to a simplified two dimensional, asymmetric convergent or CD nozzle construction, and an actuating mechanism therefore, which avoids the necessity to devote critical wing spar structural space to pneumatic load or pressure balance chambers, and wherein the nozzle may be shifted to a dry nozzle position--i.e., the cruise position--without the need for any portion of the nozzle or its actuating mechanism to move into, or otherwise interfere with, or impinge upon, the airfoil's wing spar structural space; yet, wherein the trailing edge line-of-sight into the nozzle is maintained at a minimum angle, preferably on the order of from about 2.degree. to about 3.degree. as measured from the wing chord reference plane.