Overloaded blades and lower solidities are two main characteristics of modern gas engines to reach lower specific fuel consumption and weight to thrust ratio. Hence, flow optimization methods are employed to maximize the performance. Slot treatment on blades is considered as a potential method to stand against the boundary layer separation for this issue. In the present study, the different locations of passive flow control with the slot along the compressor blade chord are simulated at four angles of attack (α), ranging from 10.93° to 28.93°. The purpose of this study is to discover the underlying reason in obtaining the best slot location, regarding the blade turning angle and total loss coefficient, in every tested inflow angle. Based on the results, the slot jet shows its utmost performance in eliminating the trailing edge separation when it is located upstream of the separation lines in the mid-span. The best slot location is able to improve the turning angle and the total loss coefficient up to 16.41% and 16.47% at 26.93°, respectively. The synthetic slot jet confines the growth of corner vortices and increases the turning angle near end walls up to 4°. In addition, the slot treatment pushes the backflow region over the suction surface up to 10% of the span toward the side walls. The importance of choosing the slot location decreases with an increase in inflow angle. However, the effect of slot locations on the performance in low angles is still considerable. With the tested blade geometry, the slotted profile in locations between 0.5 and 0.8 of axial chord length indicates a promising blade performance either in low or high angles. The slot treatment weakens the flow upstream of its location which is in contradiction with previous investigations. Two separation bubbles near the leading edge in the baseline profile have a greater size of about 2% of the blade chord for the slotted case.

叶片超载和较低的坚固性是现代燃气发动机的两个主要特征，可达到较低的单位燃油消耗和重量推力比。因此，采用流量优化方法来最大化性能。在此问题上，对刀片进行狭槽处理被认为是抵制边界层分离的一种潜在方法。在本研究中，沿狭缝沿压缩机叶片弦的被动流动控制的不同位置在四个迎角（α）范围从10.93°到28.93°范围内进行了模拟。这项研究的目的是发现在每个测试的入流角中，关于叶片旋转角度和总损耗系数，获得最佳狭槽位置的根本原因。根据结果​​，当狭缝喷嘴位于中跨中分离线的上游时，它在消除后缘分离方面显示出其最大的性能。最佳的插槽位置能够在26.93°时分别将转角和总损耗系数分别提高16.41％和16.47％。合成缝隙射流限制了角部涡流的增长，并将端壁附近的转向角增加到4°。另外，缝隙处理将吸力表面上的回流区域推向侧壁，直至跨度的10％。选择插槽位置的重要性随着流入角的增加而降低。但是，狭槽位置对小角度性能的影响仍然很大。使用经过测试的刀片几何形状，开槽轮廓位于0.5到0之间的位置。轴向弦长的8表示在低角度或高角度时都有希望的叶片性能。缝隙处理削弱了其位置上游的流动，这与先前的研究相矛盾。基准轮廓前缘附近的两个分离气泡的尺寸较大，约为开槽情况下叶片弦的2％。