波纹对高亚声叶型性能影响试验与机理分析

Based on the appearance of waves in the compressor blade processing，cascades with four kinds of waves were processed，and the plane cascade experiment was carried out，then the influences of aerodynamic performance and pressure distribution were obtained and the mechanism was analyzed. Results showed that the loss of those profiles with waves was overall larger than that of original profile. Under negative attack of angle，the influence of wave spread to the downstream and pressure side and changed the pressure distribution of profile. Moreover， the flow experienced repeated acceleration-deceleration changes on suction side of the blade where waves appeared. The width of the wave directly determined the frequency of acceleration-deceleration changes， and different initial phases of waves affected the acceleration circumstances of leading edge. The wave on suction side could change the “spike” close to the leading edge，the action mechanism for waves changing transition position was related to the characteristics of the airfoil itself; when waves occurred before the location of transition，the variation of “spike” could change the location of transition.