GB166583A - Improvements in or relating to explosive shells - Google Patents

Abstract

166,583. Wassermann, M. May 9, 1919. Projectiles.-Relates to explosive shells to which rotation is imparted during flight by means of a turbine situated in rear of, and supplied with gases under pressure from, a propellent charge in the fore part of the shell, and consists in making the extremities of the shell of streamline formation, and in locating the turbine at or near the centre of gravity zone of the shell, between the forward propellent charge and a rear bursting charge, inclined exhaust passages being provided in the peripheral wall of the shell leading from the turbine to the atmosphere. The rear portion of the shell, which normally contains the bursting charge, may be used as a storage receptacle for objects such as illuminating material or asphyxiating gas which it is desired to send to a distance. In the form shown, the shell consists of a fore part 1 containing propellent charge and, screwed to it or to an intermediate ring, a rear part 3 containing bursting charge, both parts being of stream-line formation. The turbine 13 is secured in the forward end of the part 3 by screws or rivets engaging longitudinal grooves in the casing so that the turbine is prevented from rotating, but may be projected forwardly when the shell is exploded by the bursting charge, and increase the shattering effect. The turbine 13 has wings with sharp forward edges, helicoidal upper faces 15 and lower faces 15<1> providing helical ducts between them for the gases from the propellent charge, which escape through passages 22 in the wall of the shell casing, these passages being inclined to the axis of the shell so as to impart both forward and rotary movement to it. The plug 7 in rear of the shell is screw-threaded at 10 to receive a percussion fuze. In a modification, this fuze is seated in the rear face of the turbine. The turbine has a central cavity 16 screw-threaded at 17 to receive a primer for igniting the propellent charge, the ignition being effected by a slow-match or the like in a passage 19 leading from the exterior of the casing. A rotatable ring 34 on the casing has holes 22' registering with the escape openings in the passages 22, so that the size of these holes may be regulated. The wings of the turbine may be shaped so as to provide ducts converging rearwardly as shown, or diverging rearwardly. In the form shown in Fig. 12, the propellent charge is contained in a tube 28 surrounded by a chamber 31 which may contain either propellent charge ignited through passages 33 after the charge in the tube 28 and exhausting through passages 22<111>, or bursting charge ignited through passages 32 communicating with the rearward bursting-charge.