RU2468238C1 - Engine with two-position nozzle control - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: engine with two-position nozzle control includes combustion chamber, jet nozzle and pneumatic cylinder with piston and stock, which is located in combustion chamber. On pneumatic cylinder stock end there is central body partially closing the nozzle open flow area. Each cavity of pneumatic cylinder is connected via a three-way valve to atmosphere or to gas pressure source, and namely gas bottle or gas generating grain or the combustion chamber itself or its cooling jacket. Piston, stock and central body are hollow; at that, piston has non-return valves on both ends, which are directed towards the piston cavity, and central body has injectors or nozzles. Air or gas supply pipe to rear cavity of pneumatic cylinder is located in cavity of pneumatic cylinder and passes through the piston.

EFFECT: invention allows simplifying the design of engine with two-position nozzle control.

2 dwg

Description

The invention relates mainly to liquid, but is applicable to dual-mode solid propellant rocket engines (LRE and solid propellant rocket engines).

Known liquid propellant rocket engines with an adjustable flow nozzle, see A.S. USSR No. 560077. They provide for smooth regulation of the bore and therefore have a complex structure, large dimensions and large mass. However, a smooth change in the bore is not always required. In a number of cases, for example, in air-to-air, ground-to-air, and ground-to-ground missiles, dual-mode traction control is quite enough: launch and march modes. Therefore, the nozzle control mechanics can provide for only two positions, for example, 100 and 25% of the passage section. Moreover, these cross-sections allow efficient operation in partial thrust modes, that is, in throttling modes. The result is two ranges, for example 12-25% and 50-100% of thrust, which cover its most necessary values. Moreover, in both of these ranges, engine efficiency does not fall below an acceptable level.

The objective of the invention is to simplify the design.

The technical result of the invention is on-off nozzle control.

To eliminate these drawbacks, the engine, in addition to the combustion chamber and the nozzle, contains a pneumatic cylinder with a piston and a rod, fully or partially located in the combustion chamber, at the end of which there is a central body partially covering the nozzle passage, and both cavities of the pneumatic cylinder are connected by three-way valves to the atmosphere or to a gas source pressure, which is a gas cylinder, or a gas generator, or the combustion chamber itself, or its cooling jacket. In the latter case, the component of rocket fuel used for cooling is taken slightly more, for example by 0.1%.

The central body may have cooling, which is very convenient if the cooling jacket of the combustion chamber is used as a pressure source. In this case, the vaporous oxidizing agent from the jacket is fed into one of the cavities of the pneumatic cylinder, from where through two check valves located on both ends of the hollow piston, it is fed into the piston cavity, then into the hollow rod, then into the hollow central body, from which through nozzles or small nozzles (the technical result in both cases will be the same) is thrown into the combustion chamber, where it is mixed with fuel and participates in combustion.

To do this, the piston, the rod and the central body are hollow, and the piston has check valves at both ends directed into the piston cavity, and the central body has nozzles or nozzles.

A pipe for supplying air or gas (the technical result is identical in both cases) into the rear (relative to the thrust vector) cavity of the pneumatic cylinder can pass outside the pneumatic cylinder in the cooling jacket, and can pass into the cylinder cavity, passing through the piston, see Fig. 2.

Figure 1 shows this engine, where: 1 - a combustion chamber, 2 - a jet nozzle, 3 - a pneumatic cylinder with a piston 4 and a rod 5. At the end of the rod there is a central body 6. Both cavities of the pneumatic cylinder are connected by heat-resistant pipes (shown by thick lines) with three-way valves 7 and 8. If the central body is cooled, it has nozzles or nozzles 9 (cooling system and fuel supply are not shown).

Figure 2 shows in cross section a pneumatic cylinder 3 in the embodiment with a hollow piston 4 and a rod 5. A pipe 10 passes through the piston, entering a recess in the end face of the pneumatic cylinder. The rod, piston and pipe are sealed with two piston rings 11 located in the same groove locks in different directions. In the piston cavity there are two non-return valves in the form of lever-fixed plates 12, pressed by a common thermo-corrosion-resistant spring 13 (tungsten with a titanium coating).

The engine works like this: fuel components are fed into the combustion chamber and burned out. If it is necessary to reduce draft, the fuel supply is first reduced, then the valve 8 is switched to a pressure source (cooling jacket), and the valve 7 to the atmosphere. The piston 4 is shifted to the rear (lower in the drawing) position, and the central body 6 partially overlaps the nozzle passage.

Blocking should be provided: the indicated switching of the cranes should not be possible with a fuel supply exceeding the lower draft mode, and full switching on of the fuel supply is impossible with the rear position of the central body or, more convenient, with the corresponding position of the three-way valves. In the latter case, from switching the three-way valves to “opening the nozzle” to increase the fuel supply, a certain time should pass, sufficient for the pneumatic cylinder to operate, for example 0.2 seconds.

The engine allows multiple on-off.

The invention will increase the combat effectiveness of our army aviation and navy.

Claims (1)

An engine with two-position nozzle control, comprising a combustion chamber and a jet nozzle, a pneumatic cylinder with a piston and a rod located completely or partially in the combustion chamber, at the end of which there is a central body partially covering the nozzle passage, each cavity of the pneumatic cylinder is connected by a three-way valve to the atmosphere or to a gas pressure source, which is a gas cylinder, or a gas generator, or the combustion chamber itself, or its cooling jacket, characterized in that the piston k and the central body are hollow, and the piston has check valves at both ends directed into the piston cavity, and the central body has nozzles or nozzles, the pipe supplying air or gas to the rear cavity of the pneumatic cylinder located in the cavity of the pneumatic cylinder and passes through the piston.

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