GB385942A - Internal combustion engine with rotary cylinders particularly adapted for aircraft - Google Patents

Abstract

385,942. Two stroke engines. SAMA SOC. ANON. DES MOTEURS D'AVIATION, Lechatelet-Chamblandes, Lausanne, Switzerland. March 30, 1931, No. 9665. Convention date, March 28, 1930. Void [Published under Sect. 91 of the Acts]. [Classes 7 (ii), 7 (iii), and 7 (vi).] Oppositely-moving pistons 3, 4 working with a common combustion chamber 14 in coaxial revolving cylinders carry rollers 7 which bear on a fixed oval track 9. The air for combustion is supplied by a number of pumps whose cylinders 34 revolve with the power cylinders. Valve gear.-The pumps deliver to a manifold 32 which communicates with a pair of inlet ports through ducts, the admission being controlled by valves 26; these slide inwards when rollers 28 on the valve spindles engage the track 9. Pumps.-The air pumps are driven off a cam or a swash-plate 37 ; the inclination of the plate may be varied by the hand-wheel 42, spindle 41, and roller 43, the latter bearing on a guide surface on the plate. Cylinders, cooling.-Air is blown on the revolving cylinders by a fan 21 driven in a direction opposite to the cylinder movement by bevel gear 18, 19, 20. Liquid-fuel supply.-A light and heavy fuel are supplied by a pipe 45, Fig. 5, to an inlet passage 48 controlled by a spring-pressed valve 49. The fuel nozzle 15 is integral with an extension which forms a pump plunger 51 in the chamber 52; the nozzle carries a spring- pressed block 56 having pins 58 preventing its rotation, this block and one on the revolving cylinders having corresponding cam surfaces 60, 61. As the cylinders revolve the nozzle and plunger 51 reciprocate, fuel being fed thereby to the engine. This nozzle has an internal atomizer 65.