SU10065A1 - Aircraft engine - Google Patents

Description

The invention relates to an aircraft engine in which two cylinders of different sections are applied, interconnected by means of a pipe with compressed gas, but the larger cylinder has a crank Iorshn connected to the shaft knee, and the smaller diameter cylinder is equipped with a free piston with valves for admission of combustible mixture and release of combustion products, driven by the help of levers and t r from the spring.

In FIG. 1 shows an aircraft engine in longitudinal section; FIG. 2 is a front view of the valve distribution mechanism.

An internal combustion engine consists (Fig. 1) of a large-diameter cylinder Z and a cylinder (of smaller diameter, connected to each other with a crankshaft tube N. Cylinder 2 has a piston if articulated with a connecting rod X with a shaft elbow, and cylinder G is equipped with a free piston C and valves for the intake of the combustible mixture and the release of combustion products.

I, reinforced on the wall of the cylinder and pressed by piston C during the course of the engine.

Before starting the engine, the crankshaft pipe is filled with compressed air, and then the combustible mixture is injected. When the mixture explodes, piston C pushes off, and piston M moves and drives the shaft with the help: connecting rod X. Pushed piston O releases the plate with a scare spring, and then, using the arms K and S, it closes the valve G.

The subject of the patent.

An aircraft internal combustion engine characterized by the use of a cylinder Z of larger diameter, piston M of which is articulated by connecting rod X with the shaft knee and cylinder & combustible mixture and the release of combustion products driven by means of levers and t r t, l from the spring plate g, mounted on the wall of the cylinder and pressed by the piston C.

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