GB526374A - Rotary internal combustion engine - Google Patents

Abstract

526,374. Rotary engines. TIPS, M. March 14, 1939, No. 8196. Convention date, March 18, 1938. [Class 110 (ii)] An internal combustion engine comprises a rotor 12 eccentrically positioned in a stator 10, having vanes 22 pivoted on a fixed shaft 21 which is concentric with the inner bore of the casing. The vanes slide between members 25 and co-operate with a rotary abutment 49 driven by bevel gearing, placed between inlet and exhaust ports 48, 47. The rotor is mounted in bearings 15, 16, in the casing end walls 17, 18. Members 25 are mortised cylinders provided with packing pieces 36 at the sides and edges. Packing pieces 37 in the tip of each vane are balanced centrifugally (Fig. 4) by means of a weight 39 through rocking bars 41 pivoted in fixed partitions' 38. A spring 43 presses the weight 39 inwards. An adjusting screw 45 is provided. Further packings 46, 66, 67 are provided. Combustion chambers 52 extend transversely through the rotor between each pair of vanes and terminate in ducts 53. Ducts 54 in the rotor allow compressed air, or fuel gas, to pass into a combustion chamber 52 when in augment. Packing 55 is provided, to be forced against the stator wall. When operating as a diesel engine, oil is injected through the ducts 53. Sparking plugs 57 may be used. Cooling oil is forced by a pump 59 through a pipe 61 into chambers 58 which surround the combustion chambers, and returns to the pump via ducts 65. Grooves 68 in the walls 19, 20, allow compressed air, or fuel gas, to fill chambers 52. The capacity of a compression chamber is adjusted by means of a cylinder 70 with a piston 71 on a threaded spindle which may be rotated by a handwheel. Passages 73 connect the cylinder with the interior of the engine. Where the engine is fitted to an aircraft, bullets may be fired through the hollow shaft 21.