弹用涡喷发动机起动控制规律改进研究

摘要

The missile turbojet engine' s start tests are performed on ground test system, major engine parameters and some performance parameters such as start time and surge margin are obtained. Engine' s fuel supply curve is redesigned. It is divided into three segments: fill, ignition and acceleration segment. Suitable range on fill segment and ignition segment are determined from ground tests. The results show that acceleration segment affects engine' s start performance the most. Improving fuel supply of acceleration segment will shorten start time, at the same time, reduce surge margin.%利用地面试验系统进行弹用涡喷发动机的起动试验,获得起动过程发动机各工作参数及起动时间、喘振裕度等性能参数.对发动机起动阶段控制规律进行改进试验,得到供油曲线充填段和点火段的合理范围.试验结果表明:加速段供油规律对起动性能影响较大,适当地提高加速段的供油量可以有效缩短起动时间,但同时会减少喘振裕度.