GB599275A - Improvements in nozzles for thrust motors - Google Patents

Abstract

599,275. Jet-propulsion nozzles. AEROJET ENGINEERING CORPORATION. June 23, 1945, No. 16092. Convention date, March 28, 1944. [Class 110 (iii)] The portion of an exhaust nozzle of the chamber of a thrust motor, lying inwardly of the constricted section of the nozzle, is provided with a heat-resisting lining of carbon material and preferably of compressed powdered carbon material, e.g. one or a combination of the allotropic forms of carbon such as natural graphite, flaked graphite, retort coke, petroleum coke, pitch coke or lampblack. The nozzle 3 is described as applied to a combustion chamber provided with an electric ignitor and a relief valve, the nozzle being secured against a circular shoulder on the chamber outlet, by a snap-ring which is accommodated in the recess 16. The carbon lining 21 is secured by pins 24 and the angle x thereof may be between 50 degrees and 90 degrees, an angle of 70 degrees being mentioned as satisfactory. The lining may be much thicker adjacent to the constricted section than elsewhere, but in Fig. 2 it is shown of substantially uniform thickness. Alternatively, the face of the lining may be continuously curved from the constriction to the inner end, or the lining may end short of the constriction and flush with the metal of the nozzle. The nozzle may be externally threaded to screw into a screwed socket which is welded in the mouth of the combustion chamber.