为了深入理解频率失谐对跨声速压气机气弹稳定性的影响，基于能量法建立了跨声速颤振实验转子的全周气动阻尼计算模型，数值分析了转子叶片频率交替失谐、随机失谐以及线性失谐对其气弹稳定性的影响。数值计算了该转子的气动性能，颤振边界和叶片模态，其结果和实验数据吻合较好；研究不同模态、不同叶片间相位角条件下谐调转子的气动阻尼，结果表明叶片间相位角对叶片气动阻尼均有较大的影响，尤其在一弯模态下，叶片气动阻尼对叶片间相位角最敏感；对该转子所有叶片的平均气动阻尼而言，失谐的存在弱化了叶片间相角对叶片气动阻尼的影响，显著提高了该转子最不稳定状态的平均阻尼达到 7~11倍，反之使其最稳定状态的平均阻尼降低约 50%；失谐转子中不同叶片的气动阻尼表现出显著差异，其受叶片局部失谐模式及失谐量的影响较大。

A full-annulus computational model for aerodynamic damping prediction based on energy methodis demonstrated by the consideration of a transonic flutter test rotor to improve the understanding of the influenceof frequency mistuning on aeroelastic stability of transonic compressor. The numerical analysis of alternate，ran. dom and linear frequency mistuning was performed in detail. The numerical results of rotor aerodynamic perfor. mance，flutter boundary and blade mode shape are respectively consistent with experimental results closely. Ac.cording to the aerodynamic damping of tuned rotor under the different inter-blade phase angle(IBPA)and modes，it indicates that blade aerodynamic damping is affected greatly by IBPA，especially for the first bendingmode. The blade aerodynamic damping is most sensitive to IBPA. The further investigation on various frequencymistuning modes show that，the existence of mistuning weaken the effect of IBPA on blade average aerodynamic damping. Especially，the average aerodynamic damping of all blades at the most unstable condition increasesabout 7 to 11 times. On the contrary，it decreases about 50% at the most stable condition. There are significant dif.ferences among the aerodynamic damping of each mistuned blade which is affected obviously by the blade localmistuned mode and mistuning amount.

V231.3

国家自然科学基金重点资助项目( 60934001)。