Two-component liquid propellant rocket engine combustion chamber and combustion control method

Abstract

The invention discloses a two-component liquid propellant rocket engine combustion chamber and a combustion control method, using a first propellant and a second propellant with different boiling points, and the boiling point of the first propellant is higher than that of the second propellant , from the engine head to the nozzle, the wall of the combustion chamber is divided into three parts: the protective combustion zone, the droplet crushing enhancement zone and the combustion enhancement zone. After heat exchange, it enters the propellant control area together with the second propellant, and finally enters the combustion chamber in proportion, passing through the jet flow area, the mixing area and the combustion area in sequence. The invention separates the heat generated by the propellant collision, the heat transferred from the high-temperature flame in the combustion zone to the mixing zone, and the mixing process of the propellant to the greatest extent in the time dimension. By optimizing the thermal management of the engine system and redesigning the enhanced system, the The overall performance of the engine, reducing the temperature in the collision zone, enhancing the mechanical mixing between the droplets and thus achieving a step-by-step enhancement of the liquid fuel combustion process.

Description

technical field [0001] The invention belongs to the technical field of combustion process control and thermal management, and in particular relates to a combustion chamber of a bicomponent liquid propellant engine and a method for rapid self-adaptive control of combustion. Background technique [0002] The combustion reaction process of liquid fuel and liquid oxidant in the rocket engine combustion chamber, especially the combustion in the micro and small-scale space combustion chamber, has lower combustion efficiency than that in the large-scale space, mainly because the propulsion in a narrow space The stroke of the propellant is limited, the breakage and mixing of the droplets are not sufficient, and the small-scale space before the fire is not conducive to the full mixing of the liquid propellants; in addition, after the combustion process is established, with the increase of temperature, a large amount of combustion heat will promote The low-boiling propellant evaporate...

AI Technical Summary

Problems solved by technology

[0002] The combustion reaction process of liquid fuel and liquid oxidant in the rocket engine combustion chamber, especially the combustion in the micro and small-scale space combustion chamber, has lower combustion efficiency than that in the large-scale space, mainly because the propulsion in a narrow space The stroke of the propellant is limited, the breakage and mixing of the droplets are not sufficient, and the small-scale space before the fire is not conducive to the full mixing of the liquid propellants; in addition, after the combustion process is established, with the increase of temperature, a large amount of combustion heat will promote The low-boiling propellant evaporates before the high-boiling propellant in the jet flow process between the injector outlet and the ignition point, which reduces the jet stiffness of the propellant, making the mass transfer and mixing between the propellants worse and the combustion efficiency lower

[0003] Applying the design standards and methods of large liquid rocket engines to small engines may cause engine combustion fluctuations, leading to instability in the working process; in addition, the enhancement of heat transfer inside the combustion chamber will also lead to an earlier ignition point, making the injector temperature Elevated, aggravating the instability of system combustion

In the attitude control system, to ensure the precise movement of the aircraft, the fast response characteristics of the engine are the key. This process is generally realized through the switch of the solenoid valve, but the excessively high response index puts forward more stringent requirements for the solenoid valve. The design of the valve brings greater difficulty

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