真实运行状态下叶顶间隙尺寸波动对跨声速转子气动性能的影响研究

To analyze the tip clearance size fluctuation on the aerodynamic performance of the transonic compressor rotor in actual operations, the real measurement data of tip clearance size were obtained from a transonic compressor working in a steady operating condition. The mean value, fluctuation amplitude and probability distribution of were extracted by statistical analysis. NASA Rotor 37 was chosen as research object to study the influence of the same tip clearance fluctuation at peak efficiency and near stall conditions at 100% rotating speed. Non-intrusive polynomial chaos method based on measurement data was adopted to quantify the uncertainty of aerodynamic performance. The results show that the tip clearance fluctuation has little effect on the overall aerodynamic performance but the surge margin decreases 3.75%. The transonic rotor at near stall condition is more sensitive to the tip clearance fluctuation, meanwhile, the fluctuation amplitude of the aerodynamic parameters is larger than the peak efficiency condition. The isentropic efficiency is the most sensitive parameter compared with mass flow rate and total pressure ratio. The tip clearance fluctuation affects wider range in span direction at the near stall condition compared with the peak efficiency condition. The biggest relative fluctuation amplitude of static pressure coefficient and total pressure loss coefficient at 98% span are 14.84% and 5%, respectively. The uncertainty of flow field at the peak efficiency condition is directly affected by the uncertain tip leakage flow and tip leakage flow interacting with shock wave. At the near stall condition, the uncertainty in the flow field is mainly affected by shock wave and the separation flow near the suction surface.