RU2700801C1 - Slit mixing head of liquid-propellant rocket engine chamber - Google Patents

Abstract

FIELD: engine building.

SUBSTANCE: invention relates to liquid-propellant rocket engines. Slit mixing head of liquid-propellant rocket engine chamber comprising outer bottom, housing with rings installed in it with cooling channel and holes for liquid component supply, gaps between which form annular channels for supply of gaseous component, fuel start-up nozzle, according to invention rings with cooling channels are shifted relative to each other towards chamber at distance from 0.4 part to width of annular gas channel, forming a total offset value of about 0.1÷0.3 of the cylinder cylindrical part diameter value.

EFFECT: invention provides elimination of high-frequency pressure fluctuations in the chamber.

1 cl, 1 dwg

Description

When developing a liquid-propellant rocket engine, extremely high demands are placed on efficiency and reliability. To ensure high engine efficiency, it is necessary to solve the problem of implementing the stability of the combustion process and taking measures to eliminate high-frequency pressure fluctuations in the chamber. One of the main elements that affect the economy, reliability and stability of the working process in the chamber is the mixing head.

Known design of the mixing heads, which use various measures that can ensure the stability of the working process by dividing the cavity located at the fire bottom into isolated sectors. This can be realized by extending part of the nozzles into the cavity of the combustion chamber or by installing special partitions.

A known design of the mixing head described in application No. 2007142008/06 of 11/15/2004, patent RU 23445287 C1, in which anti-pulsation partitions located on the fire bottom of the head are used to eliminate high-frequency vibrations.

The disadvantage of this design is the location of the peripheral row of nozzles near the inner wall of the chamber. The fuel components, flowing out of the peripheral nozzles, turn into combustion products in the form of gas jets that leak onto the inner wall of the chamber. As a result of the interaction of gas jets with the inner wall of the chamber, they are realized from the end of the mixing head on the wall of the chamber opposite to the peripheral nozzles of the zone with an increased ratio of fuel components, i.e. with increased temperature of hot gases in these areas. During prolonged testing, cracks, proliferations and even burnouts may appear in these areas.

The known design of the mixing head described in application No. 99124002/06 of November 15, 1999, patent RU 2170841 C1, is taken as a prototype comprising a housing with a bottom and bushings installed in them, the gaps between which form the annular channels for supplying a liquid and gaseous component.

This design allows you to provide high efficiency, increase the reliability of the inner wall of the chamber due to the location at the wall instead of the peripheral nozzles of a uniform annular channel with the components of the oxidizer and fuel. However, the design of this head does not allow the implementation of effective measures to combat high-frequency vibrations with the extension of a number of nozzles in the form of a cross in the chamber or installation of anti-pulsation partitions at the fire bottom dividing the cavity at the fire bottom into isolated sectors.

The length of these partitions should be ~ 0.1 of the diameter of the cylindrical part of the chamber. The absence of special measures to combat high-frequency vibrations, as a rule, leads to burnout of the mixing head, i.e. to emergency engine operation.

The present invention solves the technical problem of realizing the high energy characteristics of liquid rocket engines and ensures reliable operation, eliminating the possibility of high-frequency pressure fluctuations in the chamber, generally eliminating these disadvantages of the prototype. The stated technical problem is solved in that in the slotted mixing head of the chamber of a liquid propellant rocket engine containing an outer bottom, a housing with rings installed therein with a cooling path and holes for supplying a liquid component, gaps between which form annular channels for supplying a gaseous component, a fuel starting nozzle, according to the statement, the rings with cooling channels are displaced relative to each other towards the chamber at a distance from 0.4 parts to the width of the annular gas channel, forming a common the displacement is approximately 0.1 ÷ 0.3 of the diameter of the cylindrical part of the chamber.

This embodiment of the slotted mixing head of the camera allows you to implement the following processes:

1. Mixing, evaporation and combustion of the fuel components does not occur in a flat volume at the mixing head, but in a stretched volume in the form of a cone by a value of about 0.1 of the diameter of the cylindrical part of the chamber;

2. Combustion of fuel components in a volume that is variable in length eliminates the possibility of high-frequency vibrations.

The essence of the invention is illustrated by the circuit shown in FIG. one.

In FIG. 1 shows the design of a slotted mixing head, where:

1. A collector for supplying a liquid component of fuel;

2. The supply cavity of the gaseous component of the fuel;

3. The outer bottom;

4. The sleeve;

5. Track cooling;

6. Ring;

7. The hole;

8. The annular gas cavity;

9. Dosing holes of the gas component of the fuel;

10. Starting nozzle.

Slit mixing head works as follows.

In accordance with the engine operation diagram, the liquid component of the fuel enters the manifold 1, the gaseous component in the inner cavity 2 of the outer bottom 3.

From the collector 1 through the bushings 4, the liquid component is distributed into the cooling ducts 5 of the rings 6, and then through the openings 7 it enters the annular gas cavity 8.

The gaseous component from the cavity 2 through the metered holes 9 enters the annular gas cavity 8.

According to the appropriate command, the starting fuel enters the starting nozzle 10 and ignition of the fuel components occurs.

The displacement of the rings with the cooling path to a distance of 0.4 to the width of the gas cavity (depending on the size of the gas cavity) provides reliable protection of the ends of the rings to the reverse currents of gases and stretches the combustion front of the fuel components. In general, due to the displacement of the rings relative to each other, the flame front is stretched by values of ~ 0.1 of the diameter of the cylindrical part of the chamber.

Thus, the use of a slit mixing head in which the rings with cooling channels are displaced relative to each other towards the chamber by a distance from 0.4 parts to the width of the annular gas channel, forming a total displacement of about 0.1 of the diameter of the chamber of the cylindrical part of the chamber, provides a stable process of combustion of fuel components increases reliability and allows you to realize extremely high requirements for engine efficiency.

Claims (1)

A slit mixing head of a liquid-propellant rocket engine chamber containing an outer bottom, a housing with rings installed therein with a cooling path and holes for supplying a liquid component, gaps between which form annular channels for supplying a gaseous component, a fuel starting nozzle, characterized in that the rings have cooling channels are displaced relative to each other towards the chamber at a distance from 0.4 parts to the width of the annular gas channel, forming a total displacement of approximately 0.1 ÷ 0.3 diameter cylindrical part of the chamber.

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