Patent GB-146994-A (GB)
Title: Internal combustion engine with rotary compressor
IPC: F02B33/00
Filed: 1920-07-06
Abstract: 146,994. Zoller, A. June 8, 1918, [Convention date]. Fixed-abutment type; valvegear and valve-actuating mechanism; starting and stopping.- Two- and four-stroke-cycle engines for aircraft, road vehicles, &c. are charged with air or combustible mixture by rotary compressers adapted to start the engine and to stop it by braking. The compressor, Fig. 2, comprises vanes 10 equal in number to the number of cylinders and set at unequal angles to one another to produce in each cylinder the same pressure conditions during charging. The vanes 10 slide in rocking pins 9 carried by a ring 8 mounted upon the crank-shaft and rotating in a casing 14 having eccentric grooves 12, in which are guided arc-shaped extensions 11 formed on the vanes 10. The casing has an inlet orifice 16, and an outlet 18 leading to piston-controlled ports in the explosion chambers and to the supply orifice of a second compressor (not shown) for supplying high-pressure fuel-injection air. An adjustable sleeve may be mounted in the interior of the casing 14 to control the admission and delivery periods of the compressor, the adjustment being such that the final compression pressure in the cylinders remains constant irrespective of the density of the atmosphere. By mounting the pins 9 in different positions in the ring 8 the vanes 10 may be circumferentially adjusted 'relatively to casing 14. Fig. 9 shows a single stage compressor adapted to start and stop the engine and to supply air for scavenging and the injection of fuel. A threeway cock 35 places the compressor in communication, either with the atmosphere, or with a reservoir 50 charged by the compressor through a three-way valve 31. The valve 31 also places the compressor in communication with a pipe 33 leading to a high-pressure reservoir (not shown) for supplying air to accessories, or for scavenging. To start the engine, charges are admitted to the compressor from the reservoir 50 through the valve 35, stopping being effected by placing the delivery side of the compressor in communication, through the valve 31, either with the reservoir 50 or with the high-pressure reservoir (not shown). Fig. 12 shows a reversible compressor for use with an engine with may run in either direction. It comprises an adjustable sleeve 36 mounted in the interior of the casing 14, and a distributing valve 1 for reversing the functions of the passage 42, 43 serving for admission and delivery of the charge to and from the compressor. In the position of the parts shown in Fig. 12, charges are admitted to the passage 42 through the interior of the valve and enter the space between a pair of vanes during a period determined by the orifice in the sleeve 36. Compressed charges are delivered to the passage 43 when a vane commences to uncover the perforations 38, and are discharged from the compressor through the annular chamber 40 in the valve. By turning the valve through 90‹ and by adjusting the sleeve 36 the functions of the passages 42, 43 are reversed. In an engine for aircraft the blowers compress at ground level charges in excess of the capacity of the engine, the excess charges being by-passed to the suction side of the compressor.