文章数值模拟了某跨音速叶栅超音速区后附面层分别进行抽气和吹气对叶栅通道流道中超音速区位置、范围及压缩波强度的变化以及总压损失的影响.结果表明:抽气与吹气都能有效改善流道中附面层分离状况,但相比于吹气,抽气会使超音速区域向后大大扩展,使流场中出现激波,造成激波损失.从而导致整个流道中总压损失增加.这表明文中跨音速叶栅中使用抽气的方式消除附面层分离比吹气所造成的总压损失大.%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.
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