为了评估风扇/压气机在整机环境下的稳定边界,采用加源项的一维欧拉方程构建小扰动线性化的发动机整机控制方程组,建立了大涵道比涡扇发动机稳定性分析模型,利用李雅普诺夫稳定性理论,对其整机环境稳定边界进行了评估分析.计算结果表明,风扇/压气机在整机环境和单独部件环境下稳定边界存在差异.风扇整机环境稳定边界和部件环境稳定边界基本重合,整机环境稳定裕度略有减小；增压级整机环境稳定边界下移,可用稳定裕度减小；高压压气机随着换算转速降低整机环境稳定边界下移,稳定裕度减小.%In order to estimate the aerodynamic stability of fan/compressor in the turbofan engine, the high bypass turbofan engine was modeled by one- dimension Eulers equation coupling with the small perturbation method linearized the governing equation and the surge line was predicted adopting the Lyapunov stability theory. The results show that there is some difference of the stability limit between the isolated component and turbofan engine environment. Considering Fan in turbofan engine environment, the surge line is identical to the one in isolated component situation and the stability margin decreases slightly;the surge line of booster in the turbofan engine is lower, compared with isolated environment, and the stability margin reduces significantly; the difference of high pressure compressor stability limit increases and the stability margin decreases as the corrected speed reduces.
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