某航空发动机全包线气动稳定性设计方法

根据稳定性基础理论及工程经验,以某型航空发动机为例,按GJB/Z 224-2005进行了全包线气动稳定性设计,并进行了试验验证.研究结果表明:发动机在高空小表速节流状态下风扇和高压压气机的需用稳定裕度均较大;在发动机包线右边界,风扇需用稳定裕度较大,且基本一致;着陆过程受喷管亚临界影响,风扇需用稳定裕度较大.因此,这些工况在发动机设计和使用中应重点关注.在发动机气动稳定性设计时应保证风扇和高压压气机可用稳定裕度大于需用稳定裕度,并留有一定余量.采用的设计方法可以有效地满足复杂工程研制需求. 

Aerodynamic stability design method for certain aero-engine in whole engine's flight operating envelope

According to the basic theory of aerodynamic stability and engineering experience,an aero-engine,for example,aerodynamic stability design method in the whole flight envelope was presented on the basis of GJB/Z 224-2005,and some experimental verification were performed.The results show that stability margin required of fan and compressor is larger at high-altitude and low-speed state,stability margin required of fan is larger at right boundary of the engine envelope and basically remains the same,affected by the nozzle subcritical,stability margin required of fan is larger during landing.Therefore,these conditions should be focused in the engine design and use.Engine should be designed to ensure that the stability margin available of fan and compressor is greater than the stability margin required.The design method can effectively meet the demand for complex engineering development.