RU2649173C1 - Mixing head of liquid-propellant engine chamber - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: invention refers to rocket technology, namely to the liquid rocket engine that runs using the two-component fuel. Mixing head of the chamber of the liquid rocket engine, which operates according to the scheme with afterburning of the generator gas, contains the supply of generator gas, the body that has the channels for supplying the liquid component to the cavity of the mixing elements, the mixing elements that consist of concentrically connected rings, at the output of which the inclined openings are made that are connected to the supply cavity of the generating gas coming through the openings in the body, the opening in the center for the location of the ignition device, where the body with the mixing elements is a single one-piece construction, which is manufactured by the method of layer-by-layer powder laser sintering of granules, with the channel that has constant area for the supply of the fuel component.

EFFECT: invention provides for the reduced labor intensity and equipment, the exclusion of the braze welding and milling operations and for the increased reliability of the mixing head.

1 cl, 4 dwg

Description

The invention relates to rocket technology, namely to a liquid propellant rocket engine (LRE) operating on two-component fuel.

The known design of the mixing head of the chamber of the rocket engine, containing a housing, a firing plate and mixing elements located in concentric circles (RF patent No. 2127820 from 08.13.1997).

The known design of the mixing head of the combustion chamber of the rocket engine (RF patent No. 2170841 C1 of 11/15/1999), adopted as a prototype. In this design, the mixing elements are made in the form of concentric rings.

The disadvantage of this design is:

- the complexity of manufacturing (about 160 assembly units and parts);

- high complexity and equipment;

- soldering and welding;

- carrying out a large number of tests;

- increased resistance due to large hydraulic losses at the inlet and outlet along the flowing part of the head.

This invention eliminates these disadvantages of the prototype through the use of laser sintering technology of granules, which allows you to make an integral design of the mixing head.

The stated technical problem is solved using the mixing head of the chamber of a liquid propellant rocket engine operating according to a scheme for burning the generator gas, comprising a supply of generator gas, a housing having channels for supplying a liquid component to the cavity of the mixing elements, mixing elements consisting of rings concentrically connected to each other, at the outlet of which inclined holes are made, connected to the cavity for supplying generator gas entering through holes in the housing, a hole in the center for I location of the ignition device, according to the invention, the housing with the mixing elements is a single integral structure made by the method of layer-by-layer powder laser sintering of granules with a constant path over the area for the fuel component to enter.

This design allows you to get away from complex and time-consuming operations, significantly reduces manufacturing time and increases the reliability of the mixing head of the rocket engine chamber. In addition, with a constant area (due to the exclusion of input and output losses) it allows to reduce the hydraulic resistance on the head and increase its efficiency.

The essence of the invention is illustrated by the circuits shown in FIG. 1, 2, 3, 4.

In FIG. 1 shows a mixing head of a chamber made by layer-by-layer powder laser sintering of granules. The mixing head includes an inner housing 1, mixing elements 2, openings for supplying generator gas 3 to the annular cavity 4, channels for supplying the liquid component 5 to the annular cavity 6, an opening 7 for installing an ignition device. The whole structure is a single solid-state part without soldering and welding.

In FIG. 2 shows a side view of the mixing elements 2. The view shows the design of the arrangement of the openings for supplying the generator gas 3 relative to the supply channels of the liquid component 5.

In FIG. 3 is a view showing the shape of the underwater channels of the liquid component 5.

Figure 4 shows a fragment of the mixing element 2 with inclined holes 8 located therein, through which from the cavity 6 the liquid component enters the cavity 4 of the generator gas.

The mixing head operates as follows.

The generator gas after the turbine enters the gas duct (not shown) and through the holes 3 in the housing 1 is fed into the annular cavity 4.

The liquid component enters the mixing head from the inlet manifold (not shown) and through underwater channels 5 connected to the mixing elements 2 enters the annular cavity 6. After that, the liquid component through the inclined openings 8 enters the outlet to the annular cavity 4 of the generator gas, where their mixing and ignition from the ignition device (not shown) installed in the hole 7.

Thus, the manufacture of the mixing head by the method of layer-by-layer powder laser sintering of granules allows one to reduce the complexity and equipment, eliminate soldering, welding and milling operations, as well as significantly reduce the hydraulic resistance and production time and increase the reliability of the mixing head of the LRE chamber.

Claims (1)

A mixing head of a chamber of a liquid-propellant rocket engine operating in accordance with a generator gas afterburning circuit, comprising a supply of generator gas, a housing having channels for supplying a liquid component to the cavity of the mixing elements, mixing elements consisting of concentrically interconnected rings, at the outlet of which inclined openings connected to the cavity for supplying generator gas entering through openings in the housing, an opening in the center for the location of the ignition device, characterized the fact that the housing with mixing elements is a single integral structure made by the method of layer-by-layer powder laser sintering of granules with a constant path over the area for the fuel component to enter.

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