摘要
针对飞行试验中遇到的发动机在跨声速小流量状态下出现失速和喘振现象,开展了进气道和发动机相容性的分析研究.结果表明:飞行试验统计的发动机随飞行速度的失稳边界与风洞试验给出的进气道失稳边界相符,进一步证实了进气道与发动机相容性出现了问题.从进气道和发动机两个方面提出了改进措施,进气道方面通过改进斜板调节规律来扩大超声速小流量失稳边界;发动机方面通过提高最小燃油流量和放大喷口面积增加发动机空气流量和稳定裕度,该措施经验证,可以有效缓解小流量状态进气道和发动机相容性问题.进气道和发动机流量匹配设计,应增加小流量状态进气道和发动机匹配的设计准则.
The compatibility analysis of the inlet and engine was conducted, according to the phenomenon of surge and stall in state of transonic speed and low-flow during flight test. The research indicates that, the instability boundaries of the engine from flight tests agree with those of the inlet from the wind tunnel tests, proving there is something wrong in the compatibility of the inlet and engine. Two methods from the perspective of the inlet and engine were presented. One was used to adjust the inlet regulation of the ramp to enlarge the instability boundary of supersonic speed and low-flow. The other was used to increase the minimum fuel flow and the nozzle area to improve the flow and the stability margin. The validated results show that the methods can relieve the problem of inlet and engine compati- bility in low-flow. In future, the rules of inlet and engine compatibility in transonic low- flow state should be built.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第3期631-636,共6页
Journal of Aerospace Power
