叶顶间隙偏差对叶片气动性能影响的不确定性研究

The deviation between the actual processed blade and the designed blade shape inevitably occurs in the process of compressor blade manufacturing. Rotor 37 was used as the research object，and the three-dimensional constant value simulation method was adopted in order to study the effects of blade tip clearance size fluctuations on blade performance. The size fluctuation interference of the leading edge tip clearance and the trailing edge tip clearance of the blade are respectively performed based on the two-dimensional normal distribution variable generation method in the non-intrusive polynomial chaos. The effects of the uncertainty of the tip clearance on the aerodynamic performance and the uncertainty of the flow field were studied，the correlation between the tip clearance deviation within the tolerance zone and the change of aerodynamic performance was evaluated，and the mechanism of the effects of the tip clearance change on the blade stability margin was explored. The study found that the tip clearance deviation has almost no effect on the average level of blade mass flow，isentropic efficiency and total pressure ratio under equal back pressure conditions. The influence of tip clearance deviation on the standard deviation of aerodynamic performance distribution gradually increases with the approach of the operating point to the unstable boundary. At the same time，the blade tip clearance deviation will cause the sample stability margin to be reduced，and the average stability margin in the uncertainty analysis is 2.42% lower than that of the prototype blade. The tip clearance deviation mainly affects the flow field above 80% of the blade height，and the effects of the tip clearance deviation on the tip leakage flow result in the change of the blade stability margin.