SU49413A1 - Rocket engine of internal combustion - Google Patents

Description

In the proposed jet (rocket) engine, a series of increasing-volume combustion chambers connected in series are equipped with an outlet conic nozzle that removes gases while simultaneously supplying air to the narrowest part of the exit nozzle. An electric generator equipped with a propeller is installed at the mouth of this nozzle, servicing the electric heating windings protected by insulation and armor on the combustion chambers and the working nozzle.

The schematic drawing shows a longitudinal section of the engine.

In a frame / from a light metal, for example, from an aluminum alloy with rungs 2, a nozzle with an unexpanded end 5 is made, for example, made from tungsten or similar alloys. Thermal insulation b is applied over the nozzle 4, over which steel armor 7 is put, which is designed to prevent the nozzle from breaking, since the working temperature and pressure inside the nozzle are very high when the engine is running. A heating winding is superimposed on the front narrowed part of the nozzle / outside, on top of which thermal insulation is also applied with a W-shaped armor sleeve. all three chambers are superimposed heating windings 76 ,. thermal insulation 77 and armor 7P. To increase the vapor pressure of the fuel channel 18 is narrowed. A nozzle 20 is inserted into the chamber 77, through which fuel supplied through the tube 22 from the tank to the plunger pump 23 and further into the chamber 11 through the tube 27 is introduced and sprayed.

A plunger pump of the type commonly used in uncompressed diesel engines is driven by a low-powered motor 24. A chamber 75 is adjoined to the nozzle 75 of the chamber 75 by two air under the power pipes 30 with valves 57 inside. The electric nozzle 25 is mounted on the crosspiece 25 a generator 26 with a propeller 27 for supplying the heating windings of the chambers 77, 12 to 13 and an electric motor, the current of which is supplied via a wire 28 inside the frame.

The entire jet engine is enclosed outside in an aluminum casing 29. Chambers 77, 72 and 75 have gradually increased volumes. The temperature inside all three chambers is assumed to be 1000-15 ° C, depending on the height of the rise and the temperature of the injected fuel.

For additional intake of oxygen in a gaseous form, nipples 32 are inserted into the air inlet tubes, from which the tubes are led outside the casing.

When the engine is started, the current from a separate dynamo installed in the same fuse and driven from a normal-type internal-combustion engine is 0.5-1 l. c., it goes into the heating windings 76 and 8. After a few minutes, the current flows to the electric motor 24, due to which the pump starts to inject liquid fuel through the nozzle into the chamber 7 /. The volume of the chamber 77 is several times smaller than the volume occupied by the vapor due to the presence of tube J4, the pressure in chamber 77 increases dramatically. From the chamber 77, the vapor of the fuel under pressure will move into the chamber 72 and further into the chamber 13. In each chamber the pairs will expand, but since the temperature in each chamber is the same as in the first one, the temperature of the vapor at the exit from the chambers will be equal to .

The evaporating and strongly heated fuel vapors (gases) under pressure inside rush into the narrow channel J8, where they are additionally heated, and then into the nozzle 5.

The inlet gases will create a vacuum in the pipes 30, as a result of which the air rushes out of the pipes 30 into the narrow part 3 of the nozzle 4. At the same time, the fuel vapors mixed with the oxygen of the air will ignite; on one side of the hot part 3 of the nozzle 4, and with. the other is due to contact with air. Since, under these conditions, fuel vapors will burn at extremely high speeds, an explosion may occur, as a result of which the pressure from the expanded combustion products in Part 3 of the nozzle 4 will increase dramatically. In accordance with this, the gases will be directed towards the nozzle toward the expanded end 5, and upon exit they will create a large reactive force, which is directed from right to left in the drawing. The resulting reactive force will create a translational motion of the aircraft on which the engine is mounted.

After starting the engine, the electric generator 26, which is in the gas flow, will be powered by a propeller and supply the heating windings / b and electric motor 24 with the help of a propeller. After starting, the winding 8 is turned off using a switch located on the dashboard in the cockpit.

The degree of heating is controlled by a separate thermocouple, the ends of which are supplied (not shown) to the amperage control relay, and the adjustment can also be made from the cockpit.

Managing Lvigatep operation is to adjust the amount of fuel supplied by type of diesel engines.

The engine is stopped by stopping the fuel supply. The engine power (provided that the air required for burning the fuel is supplied) will increase with the lift height, since this will decrease the air resistance.

Due to the strong evaporation of the fuel, a faster and therefore more complete combustion of the fuel is achieved.

The presence of armor makes it possible to increase the pressure in the combustion chamber of part 3 without fear of an explosion, since, due to thermal insulation, an increase in the temperature in the combustion chamber will not lower the temporary resistance of the steel.

It is assumed that the explosion and the escape of gases due to the open end of the chamber of part 3 of the nozzle 4 will occur not under strictly constant pressure, but under a pulsating one. At the time of the explosion in the combustion chamber, despite the current of fuel vapor from channel 75 and the air flow from pipes 30, the pressure will increase not only towards the end 5 of the nozzle 4, but to a lesser extent towards the channel / 8. Consequently, the rate of fuel and air vapor slows down somewhat until the pressure in part 3 of the chamber decreases. Slowing the rate of fuel vapor will create increased pressure in the evaporation chambers, which will improve the subsequent pressure of fuel vapor and air. The presence of valves 51 in the pipes 30 improves the pressure build-up in the latter.

The subject matter of the invention.

.one. A jet (rocket) engine of internal combustion, characterized by the use of three or more combustion chambers 7, 12, 13 interconnected by tubes 14 and provided with an output conical nozzle (nozzle) / 5.

2. The form of the engine according to claim 1, characterized in that the combustion chamber, the tubes connecting between them, the nozzle 15 and the end 8 of the diverging nozzle are provided with windings 16 heated by electric current and covered with thermal insulation 17 and armor J9.

3. Application in the engine under item 1 of the dynamo 26, driven by the propeller 27.

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