RU2705919C1 - Liquid rocket engine chamber mixing head - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: use: for mixing fuel components. Summary of invention consists in the fact that mixing head of liquid rocket engine chamber includes housing with fuel supply cavities, components supply belts, connected to corresponding cavities of fuel components by means of channels, wherein fuel components supply belts are made in the form of shells located each relative to each other with annular gaps, and forming closed annular cavities, volume of which decreases monotonically from periphery to center, and opening into combustion chamber, wherein annular cavities of fuel components are uniformly alternating between each other, at ends of shells on the side of inlet there are end profiled bottoms, attached to each other and to housing, and forming in-series arranged annular cavities, at that insulated channels are made in said bottoms and chambers to communicate said end cavities through one another. At that said fuel chamber annular cavities are communicated with appropriate cavities to feed components via said end cavities formed by profiled bottoms.

EFFECT: higher completeness of mix formation.

1 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 a continuous increase in thrust, efficiency and improved 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.

A known mixing head of a 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, the channels connecting the cavity of the belts to the collector cavity, is installed by the input in the cavity of the collector, and the output in the cavity of the belt (RF Patent No. 2291976, application: 2005128533/06 from 09/14/2005, IPC: F02K 9/52 prototype).

The specified mixing head operates as follows. The liquid component from the reservoir cavity through the channels is fed into the holes located on the annular belts, and then into the combustion chamber. The adjustment of the flow rate of each belt of the liquid component to its flow rate to ensure the required uniformity of flow rate of the liquid component through each belt of the curtain is provided by finalizing the nozzles located in the inlet of each channel. The tubes with channels are located in different planes, which provides a small degree of clamping 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, which ensures heating of the liquid component and improves the process of mixture formation.

The main disadvantages are the complexity of the design, the insufficiently high quality of mixture formation.

The objective of the invention is to simplify the design of the mixing head with improving the quality of mixing.

The solution to this problem is achieved by the fact that the proposed mixing head of the chamber of a liquid propellant rocket engine, according to the invention, comprises a housing with cavities for supplying fuel components, supply belts of components connected to the corresponding cavities of fuel components using channels, wherein the supply belts of fuel components are made in the form of shells located with respect to each other with annular gaps and forming closed annular cavities, the volume of which monotonously decreases from the periphery to the center , and opening into the combustion chamber, moreover, the annular cavities of the fuel components are evenly alternated between each other, while at the ends of the shells on the input side, end profiled bottoms are mounted, fastened together and with the body, and forming successive end annular cavities, moreover, in the indicated bottoms and cavities are made of isolated channels connecting the said end cavities through one with each other, while these annular cavities of the fuel components are connected to the corresponding tyami supply components through said end cavities formed shaped bottoms.

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 this technical field, 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 level".

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 in FIG. 1 shows a longitudinal section of the proposed mixing head, in FIG. 2 - view of the head from the side of the fire bottom.

The proposed mixing chamber head of a liquid-propellant rocket engine comprises a housing 1 with bottoms 2 and 3 and feed cavities of the oxidizer 4 and fuel 5. The feed belts of the oxidizer 6 and fuel 7 are made in the form of several coaxially mounted shells 8, 9, 10, 11 and a central tube 12, located relative to each other with annular gaps, and forming closed annular cavities that open into the combustion chamber. The annular supply cavity of the oxidizing agent 6 and fuel 7 monotonously alternate with each other. At the ends of the shells from the input side of the components, end profiled bottoms 13, 14, 15, 16 and 17 are installed, fastened together and with the body, and forming successively located end annular cavities. In the indicated bottoms and cavities, isolated channels 18 and 19 are made connecting the said end cavities through one to another. The annular cavities of the fuel components 6 and 7 are connected to the respective cavities for supplying the components through said end cavities formed by profiled bottoms.

The proposed mixing head operates as follows.

The oxidizing agent is fed into the supply cavity of the oxidizing agent 4 and from it through the channels 18, enters the corresponding end cavities formed by the profiled bottoms 3, 13, 14, 15, 16 and 17. From these cavities, the oxidizing agent enters the annular cavities of the oxidizing agent 6 formed by the shells 8, 9, 10, 11 and the central tube 12, and of them, in the form of continuous hollow rings, with the exception of a continuous stream coming from the central tube 12, into the combustion chamber for further use.

The fuel is fed into the fuel supply cavity 5 and from it through the channels 19, enters the corresponding end cavities formed by the profiled bottoms 3, 13, 14, 15, 16 and 17. From these cavities, the fuel enters the annular fuel cavities 7 formed by the shells 8, 9, 10, 11 and the central tube 12, and from them, in the form of continuous hollow rings, into the combustion chamber for further use.

Due to the fact that the annular cavities of the oxidizing agent 6 and fuel 7 monotonously alternate with each other, when the oxidizing agent and fuel are fed into the combustion chamber in the form of annular zones, the components are mixed intensively with each other, which reduces losses associated with the imperfection of the mixing system, and thereby increasing the specific thrust of the liquid propellant rocket engine.

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

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

Claims (1)

A mixing head of a liquid-propellant rocket engine chamber, characterized in that it comprises a housing with fuel component supply cavities, component supply belts connected to respective fuel component cavities by channels, wherein the fuel component supply belts are made in the form of shells arranged relative to each other with annular gaps, and forming closed annular cavities, the volume of which monotonously decreases from the periphery to the center, and opening into the combustion chamber, and the annular the spaces of the fuel components evenly alternate with each other, while at the ends of the shells from the entrance side there are installed shaped end bottoms that are fastened to each other and to the body and form sequentially located end annular cavities, and in these bottoms and cavities there are insulated channels connecting the said end cavities through one between each other, while these annular cavities of the components of the fuel are connected to the corresponding cavities of the supply of components through the said end bones formed by profiled bottoms.

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