通常希望增压器涡轮叶轮的每个叶片都制造得完全相同，形成严格的循环对称结构，但由于制造误差和工作磨损等因素会造成涡轮叶轮存在失谐。为了在设计中降低叶轮对随机失谐的敏感性，以某型号涡轮增压器涡轮叶轮为研究对象，使用CMM缩减模型和加速Monte Carlo模拟，对使用3种有意失谐方案设计的涡轮随机失谐的敏感性进行了分析。研究表明，方案Ⅰ的叶轮强迫振动敏感性曲线仍然具有峰值特征，但振动响应幅值得到一定程度的降低。方案Ⅱ的叶轮强迫振动敏感性曲线的响应峰值不再明显，最大响应幅值放大系数相比谐调叶轮由1.86降到1.58。方案Ⅲ的叶轮强迫振动敏感性曲线上的响应峰值有较大下降，最大响应幅值放大系数为1.49，微小失谐时响应值较低，对失谐不敏感。

All turbine rotor blades are expected to be manufactured uniformly so as to form a strict circular symmetric structure, but the mistuning of turbine impeller always exists due to some factors such as the machining tolerance and running wear. In order to reduce the sensitivity of impeller to random mistuning in design,the random mistuning sensitivities of impeller designed according to three intentional mistuning patterns were analyzed based on the CMM reducedorder model and accelerated Monte Carlo simulation. The results show that the forced response sensitivity curve of pattern Ⅰ still exhibits a peak characteristic but with a decreased amplitude. The peak response amplitude of pattern Ⅱ is no longer obvious and the amplification factor of its maximal amplitude decreases from 1.86 to 1.58 when compared with the tuned turbine. The designed pattern Ⅲ results in a dramatic decrease of response amplitude and the amplification factor is only 1.49. The response amplitude of pattern Ⅲis small for slight mistuning and thus not susceptible to mistuning.