RU2291976C1 - Mixing head of chamber of liquid rocket engine - Google Patents

Abstract

FIELD: rocket engines.

SUBSTANCE: mixing head comprises housing with manifold and belts for supplying liquid component connected with the manifold through the passages arranged coaxially and defining the ring slots for supplying gas component. The inlet section of the passages that connect the spaces of the belts with the space of the manifold enter the manifold, and the exit section enters the space of the belt. The inlet section of the passages receive nozzles. The belts for supplying liquid components are provided with grooves for receiving the passages.

EFFECT: enhanced completeness of mixing.

2 cl, 2 dwg

Description

The invention relates to power plants of aircraft, and in particular to the mixing heads of the chambers of liquid rocket engines.

Most effectively, the present invention can be used to create the mixing heads of liquid rocket engines operating according to a generator circuit based on oxygen-kerosene components.

One of the main directions in the development of LRE combustion chambers is the continuous growth of thrust, economy and improvement of weight characteristics. In this case, an increase in the relative flow rate with a simultaneous increase in pressure in the combustion chamber, especially in connection with the creation of combustion chambers operating according to the scheme with afterburning of the generator gas.

A further increase in the flow rate using existing designs of the heads of the combustion chambers with a sequential arrangement of component cavities is difficult due to an increase in gas velocities in the component mixing zone, since this weakens the process of introducing liquid into the gas and reduces the efficiency of the combustion chamber.

Known mixing head of the combustion chamber of the rocket engine, containing nozzles for supplying one component, slotted channels for feeding another component, made in the form of hexagonal slots of the same thickness around the shaped outlet parts of the nozzles (French patent No. 2543222 - prototype).

In the known mixing head, the oxidizer nozzles are cantilevered in the power bottom. The oxidizing agent is fed into the nozzles from a common feed channel, made in the form of a spherical segment, in the flat part of which nozzles are installed. Fuel enters through an annular gap formed by the bottom and the wall of the combustion chamber, is redistributed by the gap between the nozzles, and enters the combustion chamber, where it is mixed with an oxidizing agent.

The main disadvantages of the mixing head are the significant hydraulic resistance along the fuel line and the increased fuel speed, caused by the clutter of the fuel path by the power bottom and the need to supply the entire fuel flow through a rather narrow annular gap, the significant uneven distribution of the fuel along the hexagonal slots, due to the fact that in the peripheral areas provides greater fuel consumption than in the central part.

The task of the invention is to remedy these disadvantages and create a mixing head of the chamber of the rocket engine with improved characteristics.

This task is achieved by the fact that, in the proposed mixing head of the chamber of a liquid propellant rocket engine, comprising a housing with a collector, supply belts of a liquid component connected to the collector by channels, arranged coaxially and forming annular slots for supplying a gaseous component, according to the invention, channels connecting the cavities belts with a cavity of the collector are installed by the inlet in the cavity of the collector, and the output in the cavity of the belt.

To provide the ability to configure each belt for a given flow rate, nozzles are installed in the input part of the channels.

To reduce the axial dimensions of the mixing head and the chamber as a whole, grooves are made in the supply belts of the liquid component to accommodate the channels.

A comparative analysis of the claimed invention with the prototype and other known solutions in the art showed that the set of features described is unknown from the existing level of technology, on the basis of which we can conclude that the technical solution meets the criteria of the invention of "novelty".

When analyzing other well-known technical solutions in the art, the features that distinguish the claimed invention from the prototype were not identified, and the set of features set out should not be explicitly for a specialist from the existing level of technology, which allows us to conclude that the claimed technical solution meets the criterion of "inventive step" "

The compliance of the proposed technical solution with the criterion of "industrial applicability" follows from the following example of a specific embodiment of the mixing head of the rocket engine chamber.

The invention is illustrated by drawings, where figure 1 shows a longitudinal section of the proposed mixing head, figure 2 is a left view.

The main elements of the proposed mixing head are:

1 - housing;

2 - collector;

3 - tubes;

4 - channels;

5 - ring belts;

6 - holes;

7 - jets.

The mixing head has a housing 1 with a manifold 2. Inside the housing 1, on the tubes 3 with channels 4, annular belts 5 are concentrically arranged, in which openings 6 are made for supplying a liquid component. At the input of the channels 4, nozzles 7 are installed.

The proposed mixing head operates as follows.

The liquid component from the cavity of the manifold 2 through the channels 4 is fed into the holes 6 located on the annular belts 5, and then into the combustion chamber. The adjustment of the flow rate of each belt of the liquid component to its flow rate in order to ensure, therefore, the required uniformity of flow rate of the liquid component through each belt of the curtain is provided by finalizing the nozzles 7 located in the input part of each channel 4.

Tubes 3 with channels 4 are located in different planes, which provides a small degree of compression of the cross section and, therefore, a reduced gas velocity in the mixing zone.

The generator gas is supplied through axial annular slots formed by concentrically arranged belts 5, which ensures heating of the liquid component and thereby improves the process of mixture formation.

Reduced gas velocities and the possibility of increasing the flow rate of the fluid with low losses can significantly increase the degree of introduction of fluid into the gas and thereby improve mixture formation.

Using the proposed technical solution will allow you to create a mixing head, providing increased completeness of mixture formation at a reduced speed of the generator gas.

Claims (3)

1. The mixing head of the chamber of a liquid propellant rocket engine, comprising a housing with a manifold, supply belts of a liquid component, connected to the collector by channels, arranged coaxially and forming annular slots for supplying a gaseous component, characterized in that the channels connecting the cavity of the belts to the collector cavity, installed inlet in the cavity of the collector, and the output in the cavity of the belt. 2. The mixing chamber head of a liquid propellant rocket engine according to claim 1, characterized in that the nozzles are installed in the inlet part of the channels. 3. The mixing chamber head of a liquid-propellant rocket engine according to claim 1, characterized in that grooves are made in the belts to accommodate the channels.

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