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

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.

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