Liquid-propellant rocket engine

FIELD: rocket and space engineering.

SUBSTANCE: proposed liquid-propellant rocket engine has chamber. Bypass main line with flow rate regulator passing part of fuel into chamber by-passing cooling duct is installed in parallel to line of fuel delivery for cooling.

EFFECT: increased service life of engine chamber owing to reduction of thermal stresses in inner wall.

1 dwg

 

The invention relates to rockets and engine and can be used in the development of liquid rocket engines reusable.

Famous rocket engine with regenerative cooling system of the camera, inside each cooling channel which is formed at least one protruding rib that is designed to enhance heat removal from the chamber walls (U.S. patent No. 4781019, IPC F 02 K 9/00).

However, this solution does not resolve the occurrence of thermal stresses in the inner wall of the chamber, caused by the change in thermal condition of the chamber walls due to throttling of the engine through the channels of traction and ratio of components.

The closest in technical essence (prototype) of the present invention is a liquid propellant rocket engine (see Meekeluk "Theoretical basis for the design of liquid propellant rocket engines". - M.: Barongis, 1960, s, Fig)containing chamber regenerative cooling system and the liquid zone of the veil, the turbopump feed system components in the chamber and the gas generator, the control system with traction control and ratio controller components.

Although this engine and provides heat mode cavity design through the use of zones of liquid veil inside the second wall of the fuel however, the camera of this engine is not protected from the resulting thermal stresses in the inner wall caused by the change in thermal design of the camera due to throttling of the engine in flight through the channels of traction and ratio of components. As a result of joint deformation of the chamber walls in their material having a large thermal stress, which can cause multiple loading design and to increase the share of accumulated during each cycle of damage, which leads to a sharp drop in resource camera.

The objective of the invention is to provide a liquid-propellant rocket engine, providing the technical result consists in increasing the resource of the camera by reducing thermal stresses in the inner wall due to the regulation of the engine.

This technical result in liquid-propellant rocket engine containing chamber regenerative cooling system and the liquid zone of the veil, the turbopump feed system components in the chamber and the gas generator, the control system with traction control and regulation of the ratio of components is achieved by the fact that it is parallel to the line of feed of fuel to the cooling chamber installed air line with flow regulator, perepuskajutsja of the fuel in the chamber, bypassing the cooling channel.

On with the Birmingham shows the proposed liquid propellant rocket engine.

The engine consists of a chamber 1 with regenerative cooling system and the liquid zone of the veil, turbopump Assembly, including the gas generator 2, a turbine 3, the oxidizer pump 4, the fuel pump 5, the control system with traction control 6 arranged in line 7 of the fuel in the gas generator 3, and the ratio controller components 8 that are located in line 9 of the fuel in the cooling chamber 1, which is set in parallel connection of main cable line 10 with flow regulator 11, perepuskajutsja of the fuel in the chamber 1, bypassing the cooling channel 12.

The engine works as follows. During operation of the engine is put through numerous commands from the control system to regulate the thrust and the ratio of components that are executed by the traction control 6 and ratio controller components 8. Regulation of the engine changes the costs and the temperature of the flow of products of combustion in the chamber 1 and the cooling fluid (fuel) in the cooling channel 12, which causes the deviation from the steady-state values of the conditions of the heat supply to the internal wall of the chamber 1 and the heat sink conditions from it that leads to a change in temperature of the inner and outer walls of the chamber. At this point turns on the flow regulator 11 in the bypass line 10, perepuskajutsja of the fuel in the chamber 1, bypassing tractoare 12. The flow regulator 11 operates in dependence on control commands generated in such a way as to counter the change of conditions of heat supply to the inner wall due to the regulation of the engine, the change in the flow rate of fuel in the bypass line. This change of flow in the bypass line leads to the change of fuel consumption in the channels of the cooling channel, resulting in a change in the value of the coefficient of heat transfer into the coolant, which generally changes the heat flow into the chamber design and, accordingly, changes the temperature of the internal (fire) wall of the chamber. From the foregoing it is seen that the flow regulator 11 in the bypass line 10 is designed to stabilize thermal and stress state of the design of the chamber 1, which reduces races thermal stresses in the inner wall of the chamber, eliminates multiple loading design and reduces the accumulated damage in the inner wall, which generally increases the life of the motor chamber.

Thus, in the operation of the proposed flow control valve in the bypass line, perepuskajutsja of the fuel in the chamber, bypassing the cooling channel, the negative impact of thermal stresses caused by the regulation of the engine thrust and the ratio of components will be reduced to insignificant urovnem stabilization thermal and stress state of the design of the chamber. It provides the technical result consists in reducing thermal stresses in the inner wall and the increase of resource chamber liquid propellant rocket engine.

Liquid propellant rocket engine containing chamber regenerative cooling system and the liquid zone of the veil, the turbopump feed system components in the chamber and the gas generator, the control system with traction control and ratio controller components, characterized in that parallel to the fuel line to the cooling chamber installed air line with flow regulator, perepuskajutsja of the fuel in the combustion chamber, bypassing the cooling channel.



 

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