半开式富氧补燃混合循环发动机方案研究

Scheme Investigation on a Half Open Oxygen-Rich Staged Combustion Mixture Cycle Rocket Engine

关键词:  液体推进剂火箭发动机  混合循环  富氧补燃  系统方案  液氧煤油

Key words:  Liquid propellant rocket engine  Mixture cycle  Oxygen-rich staged combustion  System scheme  Liquid oxygen and kerosene

摘要:

针对未来航天主发动机的应用需求，提出了一种燃料供应系统采用开式循环、氧化剂供应系统采用分级燃烧闭式循环的半开式富氧补燃混合循环发动机系统方案，综合分析了这种新型混合循环发动机所能达到的比冲性能，对比分析了新型混合循环发动机作为可重复使用航天运载器主发动机相比于开式循环和常规补燃循环、全流量补燃循环发动机的优缺点，针对推力为100t级的液氧煤油混合发动机的系统进行计算和分析。结果表明，新型混合循环发动机在主燃烧室压力26.5MPa下，海平面比冲可以达到303s，可以以较小的比冲性能损失为代价，实现涡轮泵介质相容、有效提高发动机设计裕度。

Abstract:

Aiming at the applications for space launch vehicle main engines， a half open oxygen-rich staged combustion mixture cycle engine scheme，with which an open fuel supply subsystem and an closed oxygen supply subsystem are applied， is proposed in this paper. The specific impulse performances of this kind of mixture cycle are calculated， and comparing with open cycle， convention closed cycle and full flow closed cycle， its advantages and shortcomings are discussed from the viewpoint of being used as reusable space launch vehicle engines. The detail system parameters for a 1000kN thrust level liquid oxygen kerosene mixture cycle engine are calculated. The results show that for the new mixture cycle engine， sea level specific impulse can attain 303s under the main combustion chamber pressure of 26.5 MPa. Meanwhile， its high critical design margin， along with the compatibility of turbo-pump mediums， can be obtained at the cost of a small loss of specific impulse.