Numerically exploring effects of boundary layer air suction and air blowing in transonic cascade

Aim. To our knowledge, there is no paper in the open literature dealing with the subject matter mentioned in the title. Sections 1, 2 and 3 of the full paper present our numerical exploration results of the effects of air suction and air blowing of the boundary layer behind the supersonic area in a transonic cascade on: (1) the changes in the location and range of supersonic area, (2) the intensity of compressive wave, (3) the total pressure loss in the flow field. The core of section 2 is that we divide the flow field into three areas, which are shown in Fig. 3, and analyze the total pressure loss in each area. Section 3 presents our simulation results, which are given in Figs. 5 through 12; the simulation results and their analysis show preliminarily that: (1) air suction and air blowing can effectively reduce the separation of the boundary layer flow; (2) compared with air blowing, air suction may make the supersonic area larger in the rearward direction and produce shock waves in the flow field, which may increase the total pressure loss. We conclude from the simulation results that the total pressure loss caused by the boundary layer separation reduction in the transonic cascade is greater for air suction than for air blowing.