GB731739A - Burners for use with rocket motors - Google Patents

Abstract

731,739. Rocket motors. ARMSTRONG WHITWORTH AIRCRAFT Ltd. Sir W. G. Dec. 18, 1953 [March 2, 1953], No. 5715/53. Class 110 (3). [Also in Group XII] In a rocket motor which operates with a fuel and an oxidizer as the propellant ingredients, the ingredients are supplied through a spray device comprising two spaced coaxial metal plates 11, 12 secured together at a number of points, at least one of the plates 11 being secured directly or indirectly near its outer edge 'to the combustion chamber 16 of the rocket motor to form the end wall thereof. One of the propellant ingredients, say the fuel, is supplied to the chamber from a space 20 outside the other plate 12 through holes 21 formed at the points where the two plates are secured together. The other ingredient, the oxidizer, is supplied from the space 25 between the plates through holes 28 in the first plate 11. In Fig. 1 a dished annular plate 18 is secured to the plate 12, fuel being supplied to the space therebetween before passing through the holes 21. The oxidizer is supplied to the space 25 from a channel 27 and the holes 28 from which it discharges are inclined so that the jets of oxidizer will intersect the jets of fuel from the holes 21. A number of ways in which plates 11, 12 may be secured together are described. The plates may be formed with depressions 35, 36 as shown in Fig. 1, the abutting surfaces of the depressions being connected by welding or the like or by means of rivets which are drilled to provide holes 21. One of the plates may be formed with depressions by pressing and the 'other machined to form depressions, or the two plates may both be flat and connected by means of ferrules 48, Fig. 7, which are formed with holes 21 and 28 and with a recess 35.