摘要
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。
The missile turbojet engine＇ s start tests are performed on ground test system, major engine pa- rameters 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.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2012年第3期313-317,共5页
Acta Armamentarii
基金
航空科学基金和航空电子系统综合技术国防科技重点实验室联合项目(20095584006)
关键词
飞行器实验技术
涡轮喷气发动机
起动
控制规律
experimental technology of aerocraft
turbojet engine
start
control discipline
