基于闭式补燃循环液体火箭发动机流量大的特点，欲设计效率水平高的航天反力式涡轮。
Attributing to the large flow rate, high efficiency level reaction turbine is adoptive in staged combustion cycle liquid rocket engine.
气液同轴直流离心式喷嘴对补燃发动机燃烧室高频燃烧稳定性有显著影响。
The bipropellant gas-liquid coaxial orifice-swirl injector has great effects on the high-frequency combustion instability of the LOX/kerosene staged combustion cycled engine.
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