Experimental Study on the Effect of Leading-Edge Curvature Optimization on Pressure Fluctuations in Transonic Compressor Blades

To investigate the impact of continuous leading-edge curvature on the aerodynamic performance of transonic compressor blade profiles, schlieren observations and surface pulsating pressure measurements were conducted on the baseline profile CM1.2 and its optimized variant CM1.2-Y. The results indicate that the optimized profile can effectively reduce unsteady pressure pulsations at Mach numbers of 0.8 and 1.05, with a maximum reduction of 14.6 dB. At Mach number 0.95, the optimized design eliminates high-pressure pulsation regions on the pressure surface but intensifies local loading on the suction surface. The optimization of leading-edge curvature effectively reduces the extreme pulsations on the suction surface caused by shock wave interference under most operating conditions, and significantly improves the wave structure on the pressure surface, thereby comprehensively reducing the pressure pulsation level of the blade profile.