RU2291975C1 - Mixing head of chamber of liquid rocket engine - Google Patents

Abstract

FIELD: rocket engines.

SUBSTANCE: head comprises nozzle for supplying one component and slot passages for supplying second component. The supplying passages connected with the nozzles are arranged in several planes. A part of the nozzles is arranged radially, and the other part of the nozzles are arranged at the sides of the triangles between the radii and are rigidly connected with the grate providing with axial slots for flowing gas component. The exit sections of the nozzles are in the same plane. The grate is provided with load-bearing fins.

EFFECT: reduced hydraulic drag and improved fuel distributing.

2 cl, 4 dwg

Description

The invention relates to power plants of aircraft, namely, 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 head containing nozzles for supplying one component, slotted channels for supplying another component, according to the invention, the supply channels connected to the nozzles are located in several planes, and one part of them is located along several radial rays, and the other on the sides of the triangles between them, rigidly connected by a lattice having axial slots for the passage of the gaseous component. The output sections of the nozzles are located in the same plane.

To increase the rigidity of the structure, power ribs are installed on the grate.

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 diagram of the proposed mixing head, figure 2 is a cross section, figure 3 is a left view, figure 4 is a right view.

The main elements of the proposed mixing head are:

1 - oxidizer nozzle;

2 - supply tubes;

3 - feeders;

4 - feeders;

5 - feeders;

6 - feeders;

7 - stiffness lattice.

The required number of nozzles of the liquid component 1 having different lengths are set in the oncoming flow of the generator gas. The fluid is supplied to the nozzles through the supply tubes 2, which are mounted on special feeders 3, 4, 5, 6, providing a constant flow rate through the nozzles.

The necessary strength and rigidity is provided by the use of stiffeners welded to the feeders 6, and the use of a stiffener 7, which simultaneously performs the functions of a leveling and stabilizing device.

The proposed mixing head operates as follows.

The liquid component is supplied to the nozzles 1, having different lengths, through the supply tubes 2, which are installed on special feeders 3, 4, 5, 6, providing a constant flow rate through the nozzles. From the nozzles, the oxidizing agent is fed into the combustion chamber.

Feeders 3, 4, 5, 6 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.

Generator gas is supplied through axial annular slots formed by feeders 3, 4, 5, 6, which ensures heating of the liquid component and thereby improves the process of mixture formation.

In the proposed direct-flow head design, various types of nozzles — jet, centrifugal, and slotted — can be used.

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.

In the case of using an engine circuit with one gas generator, there is no need to use any structural elements for supplying gas in the proposed direct-flow head.

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 containing nozzles with supply channels for supplying one component, channels for supplying another component, characterized in that the nozzles have different lengths and are located in several planes, with one part of the nozzles located along the rays and the other on the sides of geometric figures, for example triangles, between radial rays, a rigidly connected lattice having axial slots for the passage of the gaseous component. 2. The mixing head according to claim 1, characterized in that the output sections of the nozzles are located in the same plane. 3. The mixing chamber head of a liquid propellant rocket engine according to claim 1, characterized in that power ribs are installed on the grate.

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