RU2703889C1 - Lpe combustion chamber mixing head - Google Patents

Abstract

FIELD: rocket equipment.

SUBSTANCE: invention relates to the field of rocket equipment and can be used in the construction of the liquid-propellant engines (LPE) combustion chambers mixing heads. LPE combustion chamber mixing head consists of a body with bushings made therein, gaps between which form the gaseous component supply annular channels. Mixing elements are fitted into said mixing head and secured at outlet ends of bushings. Bushings are interconnected by means of bypass channels. Each bushing consists of an outer and an inner rings, interconnected by evenly spaced inclined or straight ribs, between which the liquid component supply slots are located. Much of the liquid component is fed into the central bushings via one annular header, while the smaller part is fed into the peripheral bushing via the other annular header, at the inlet of which a tuning washer is installed.

EFFECT: invention provides higher reliability of cooling of combustion chamber and reduced cost and time of LPE.

1 cl, 2 dwg

Description

The invention relates to the field of rocket technology and can be used to create the mixing heads of the combustion chambers of liquid rocket engines (LRE).

Currently, one of the main problems in creating a rocket engine is to ensure reliable cooling of the combustion chambers. One of the ways to ensure reliable cooling is to ensure the optimal ratio of fuel components in the parietal layer formed by the peripheral row of the mixing elements of the head.

Known mixing head of the combustion chamber of the rocket engine, containing a housing with a bottom and bushings installed in it, the gaps between which form the annular channels for supplying liquid and gaseous components. Into said mixing head are introduced mixing elements fixed to the output ends of the bushings. The bushings are interconnected bypass channels. Each mixing element consists of two rings concentrically connected to each other, on one of the inner surfaces of which two screw threads are made with the formation of a collector between them. The collector is connected by inclined holes to the supply channels of the gaseous component, (US Pat. RU No. 2170841, application No. 99124002/06 of 11/15/1999).

In such a mixing head, all the fuel is supplied to a common manifold located on the power bottom, and then through the bypass channels to the mixing elements, including the mixing elements of the peripheral row. Ensuring a given distribution of fuel among the mixing elements in such a head due to its complexity requires a large amount of experimental testing in the manufacturing process. In this case, if it becomes necessary during the LRE firepower development to improve cooling of the internal wall of the combustion chamber by changing the ratio of fuel components in the peripheral row of the mixing head elements, it is necessary to change the diameter of the holes of the mixing head, which increases the time and cost of working out.

The objective of the present invention is to increase the reliability of cooling the combustion chamber and reduce the cost and time of working out the rocket engine.

This problem is achieved by the fact that the mixing head of the LRE combustion chamber contains a housing with bushings made in it, the gaps between which form the annular channels for supplying the gaseous component. Into said mixing head are introduced mixing elements fixed to the output ends of the bushings. The bushings are interconnected bypass channels. Each sleeve consists of outer and inner rings interconnected by evenly spaced inclined or straight ribs, between which there are grooves for supplying the liquid component.

Most of the liquid component is fed into the central bushings through one ring collector, and a smaller part is fed into the peripheral sleeve through another ring collector, at the inlet of which a tuning washer is installed.

The essence of the proposed invention is illustrated by drawings, where in FIG. 1 shows a general view of the mixing head and a circuit for supplying gaseous and liquid components, FIG. 2 - bushings and gas channel.

The mixing head includes a housing (1) with central bushings (2) made therein and a peripheral sleeve (11) forming concentrically arranged channels of the liquid (3) and gaseous (4) components. The bushings forming the channels of the liquid component are interconnected by bypass channels (5). Each sleeve consists of an inner (6) and an outer ring (7), interconnected by evenly spaced inclined or straight ribs (8), between which there are channels (3) for supplying the liquid component. At the output ends of the outer and inner rings of the bushings there are inclined or straight holes (9) connected to the supply channels of the gaseous component.

Most of the liquid component is fed into the central bushings through one annular manifold (10), and a smaller part is fed into the peripheral sleeve (11) through another annular manifold (12), at the entrance of which there is an overlay (13) and a tuning washer (14).

The proposed mixing head works as follows:

The gaseous component enters the channels of the gaseous component (4) located between the bushings (2).

Most of the liquid component enters the annular manifold (10), then to the bypass channels (5), then to the channels (3) formed by the outer and inner rings of the central bushings and then goes to the output ends of the bushings in the holes (9).

A smaller part of the liquid component enters the annular manifold (12), at the entrance to which there is a plate (13) with a tuning washer (14), and then to the peripheral sleeve (11) with holes.

Through holes (9), the liquid component enters the gas channels, where it burns with the gaseous component.

If it becomes necessary to improve the cooling of the internal wall of the combustion chamber during firing of the rocket engine by changing the ratio of the fuel components in the peripheral row of the mixing elements of the head, another tuning washer (14) is installed in the overlay (13), which ensures the required flow rate of the liquid component. This does not require changing the diameters of the holes (9) and re-testing the hydraulic characteristics of the mixing head.

Thus, the combination of new features that are absent in the known technical solutions can improve the reliability of cooling the combustion chamber and reduce the cost and time of working out the rocket engine.

Claims (2)

1. The mixing head of the LRE combustion chamber, comprising a housing with bushings made therein, gaps between which form annular channels for supplying a gaseous component, and each sleeve consists of outer and inner rings interconnected by evenly spaced inclined or straight ribs, between which there are channels the supply of the liquid component, while at the output ends of the outer and inner rings of the bushings there are inclined or straight holes connected to the supply channels of the gaseous component, o characterized by the fact that two annular collectors are made in the head housing, while one annular collector is connected bypass channels to the central bushings, and the second to the peripheral bush. 2. The mixing head of the LRE combustion chamber according to claim 1, characterized in that a tuning washer is installed at the entrance to the annular manifold connected to the peripheral sleeve.

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