摘要
基于可调斜板式进气道及涡扇发动机,研究了飞机高空超声速减速条件下,进气道斜板板位快速调零后涡扇发动机的喘振特征,及放大尾喷口临界截面面积和提高风扇转速的扩稳措施对发动机稳定性的影响。结果表明:进气道可调斜板快速调零引起的发动机进口压力波动,会导致进气道与发动机流量不匹配,进气畸变增大;较低风扇换算转速下,进气畸变等降稳因子会导致发动机稳定裕度不足;放大尾喷口临界截面面积,提高了发动机的稳定性,喘振概率大大降低;增加最小燃油流量,提高高空发动机慢车状态风扇转速,可避免发动机进入低转速易喘振区域。
Based on the adjustable ramp inlet and turbofan engine, the surge characteristics after the inletramp position fast adjusted to zero, and the effect of enlarging the exhaust nozzle throat area and increasingthe fan speed to the engine stability was investigated during the flight speed reduction in high-altitude su?personic condition. The results indicate that, firstly, the inlet ramp position fast adjusted to zero will lead tothe fluctuation of engine inlet pressure, the flow in the inlet duct and engine will not match, and the intakedistortion will increase. Secondly, the intake distortion and other factors will result in the lack of enginesurge margin with the low fan speed. Thirdly, the enlargement of the exhaust nozzle throat area will increasethe engine surge margin and the probability of surge will decrease greatly. Fourthly, increasing the mini?mum fuel flow will improve the fan speed in idle, and prevent the engine from incidental surge region.
作者
申世才
郝晓乐
贾一哲
SHEN Shi-cai;HAO Xiao-le;JIA Yi-zhe(Engine Flight Test Technology Institute of Chinese Flight Test Establishment,Xi’an 710089,China)
出处
《燃气涡轮试验与研究》
北大核心
2016年第3期7-10,48,共5页
Gas Turbine Experiment and Research
关键词
涡扇发动机
喘振
进气道可调斜板
尾喷口临界截面面积
风扇转速
扩稳
飞行试验
turbofan engine
surge
the adjustable ramp inlet
exhaust nozzle throat area
fan speed
enlarge the engine surge margin
flight test
