现如今，涡轮负荷的提升将带来更大尺寸的分离，因此控制涡轮叶栅流动损失成为研究的重点。本文采用仿生学球形凹坑表面结构被动控制方法，探究了5种深度的凹坑方案，分别是0.1mm、0.15mm、0.2mm、0.25mm和0.3mm，深径比均为0.25，三排凹坑被布置在18%-30%弦长处，其中距叶片吸、压力面分别为2mm，轴向间距为4mm。研究对象为1+1/2高压级跨声速对转涡轮构成的平面叶栅，通过商用CFD模拟计算得出的损失系数，静压分布等气动指标，分析在端壁λ置布置不同深度凹坑对涡轮叶栅流动性能的影响。数值结果显示：0.2mm深度的端壁凹坑对流道内涡系发展具有最优的流动控制效果，抑制横向二次流沿展向爬升，削弱端区附近激波强度，使叶栅总压损失系数降低2.71%。

The passive control method of  bionics dimple  surface structure wa  adopted to explo re fiv e dim ple sc heme s with different depths, which were 0. 10 mm, 0. 15 mm, 0. 20 mm,  0. 2 5 mm  and 0 . 30  mm re sp ectively.  The  depth dia me ter ratio was 0. 25, and three rows of dimples were arranged at 18% ~30% ch ord lengt h,  in w hich th e di st ance f rom  the  suctio n and pre ssur e s urface s of t he blades was 2 mm, and the ax ial spac- ing was 4 m m. Th e re search ob ject was the plan e ca scade compose d of 1+1 / 2 hi gh press ure transoni c tur bine. The aero- dynamic in dexes such as loss coefficient and st atic pressure dist ribu tion were o btained b y com merc ial CF D si mulation, and the influen ce of dif feren t depth pit s on the flow p erform- ance of t urbi ne c asca de wa s an alyze d. The nu meric al r esults sho w that the 0. 2 mm deep e nd wall pi t has th e best flow con- trol effe ct o n the d evelopmen t of v ortex syst em in the channel,  inhibits th e lateral seco ndary flow clim bing alon g th e span wise directio n, w eake ns the sho ck in tensity nea r th e en d zone, and reduces the total pressure loss coefficient of the cascade by 2. 71 %.