为了减小从康达喷气叶栅内部流出的喷气方向与叶栅主流方向的偏差，进一步提升康达喷气对流动分离的抑制效果，本文基于流体拓扑优化技术及布置导流肋的方法对康达喷气叶片原始喷气内腔结构进行优化设计。采用数值计算和高速风洞试验评估优化的喷气内腔结构对康达喷气叶栅气动性能的改善效果。结果表明：优化设计的带肋喷气内腔结构可以减小康达喷气与主流掺混的偏差角，叶片吸力面尾缘的流动分离区域进一步减小；在来流Ma为0.5、攻角为0°、1.25%喷气量下，采用带肋喷气内腔的康达喷气叶栅总压损失系数较采用原始喷气内腔结构降低了7.15%；采用带肋喷气内腔结构能够使叶栅在不同工况条件下的总压损失小于原始内腔结构，且在最佳喷气量下获得最小的总压损失系数。

In order to reduce the deviation between the jet direction outflowing from the inside of Coanda jet cascade and cascade mainstream direction, and further improve the inhibition effect of Coanda jet on flow separation, the structure of the original Coanda jet cascade bleed air cavity was optimized in this paper, based on the fluid topology optimization technology and the guide rib layout method. A numerical calculation and a high speed wind tunnel test were used to evaluate the enhancement effect of the bleed air cavity structure optimization on the aerodynamic performance of Coanda jet cascade. Results show that the optimized ribbed bleed air cavity structure can reduce the angle of deviation between the Coanda jet and the mainstream mixture, and the flow separation area of the trailing edge of the suction surface of the blade is reduced further; with an inflow Ma of 0.5, an angle of attack of 0° and a jet mass flow ratio of 1.25%, compared to the original bleed air cavity structure, the total pressure loss coefficient of the Coanda jet cascade with a ribbed bleed air cavity is decreased by 7.15%; the use of a ribbed bleed air cavity structure can make the total blade pressure loss of cascade under different operating conditions lower than that of original cavity structure, and the minimum total pressure loss coefficient is obtained at the optimal jet mass flow ratio.

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国家自然科学基金（52206061）;国家重大科技专项（2017Ⅱ00040017，J2019Ⅱ00170038）；航空发动机及燃气轮机基础科学中心项目（P2022AⅡ002001）