进气畸变下两级跨声风扇失速预测与试验研究  

Experimental and prediction of stability of a two-stage transonic compressor with inlet flow distortion

作　　者：孙大坤[1] 杨进飞 李运 吴俊 孙晓峰[1,4] 冀国锋 SUN Dakun;YANG Jinfei;LI Yun;WU Jun;SUN Xiaofeng;JI Guofeng(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;AECC Guiyang Engine Design and Research Institute,Guiyang 550081,China;Haizhuang Guangzhou Bureau,Guangzhou 510000,China;Research Institute of Aeroengine,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]中国航发贵阳发动机设计研究所,贵阳550081 [3]海装广州局,广州510000 [4]北京航空航天大学航空发动机研究院,北京100191

出　　处：《燃气涡轮试验与研究》2025年第2期91-99,共9页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(U2441279,52325602)。

摘　　要：为进一步研究进气畸变条件下压缩系统的稳定性、提高工程研制效率和缩短设计迭代周期,基于可压缩流动稳定性解析模型对某两级风扇部件气动稳定性开展了压力畸变试验测试和失稳预测,评估了不同转速和不同进气条件下的风扇性能,并针对设计点工况开展了失稳预测与试验对比分析。结果表明:综合畸变指数为12%时,进气畸变条件下的工作点参数与均匀条件下相比,无量纲化总压比降低约0.029、效率降低2.7%,稳定裕度损失15.2%;在设计转速时,风扇剩余裕度最小,为6.71%;探明了风扇部件在严苛条件下的稳定工作能力。理论模型较好地预测了风扇部件在均匀进气条件与畸变来流条件下的失速点,且与试验结果较为接近,表明该理论模型对于指导工程设计迭代优化具有较高的应用价值。To further investigate the stability of compression systems under inlet distortion conditions and enhance engineering development efficiency while reducing design iteration cycles,a three-dimensional compressible steady-state model was employed to conduct pressure distortion test measurements and instability predictions on the aerodynamic stability of a two-stage fan component.Evaluations of fan performance were carried out under varied rotational speeds and inlet conditions,andinstability predictions and experimental analyses were performed for design-point operating conditions.The results reveal that under inlet distortion conditions,when the overall distortion index W=12%,the working-point parameters exhibit a decrease of approximately 0.029 in dimensionless total pressure ratio and a 2.7%reduction in efficiency,accompanied by a 15.2%loss in stability margin.Notably,at the design-point rotational speed,the fan achieves a minimal residual margin of 6.71%,thereby elucidating its stable operational capability under severe conditions.The theoretical model demonstrated a high degree of accuracy in predicting the stall points of the fan component under both uniform inlet and distorted inflow conditions,with predictions closely aligned with experimental results.This underscores the model’s significant practical value in guiding engineering design iteration and optimization,thereby enhancing the robustness and reliability of fan components in challenging operating environments.

关 键 词：航空发动机 进气畸变 风扇部件 畸变装置 稳定性 数值模拟 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]