为解决燃气轮机涡轮在端区二次流动造成的流动损失，对叶身/端壁融合(Blended Blade and End Wall，BBEW)技术在涡轮气动优化中的有效性进行研究，以E3模型高压涡轮第一级叶栅为研究对象，对涡轮叶片吸力面下端壁进行不同形式的叶身/端壁融合造型。设置入口总温为709 K，总压为344.74 kPa。通过数值模拟研究叶身/端壁融合技术在降低端壁气动损失及提高涡轮级效率和做功能力方面的贡献。研究结果表明：融合技术的应用能够有效减少端区局部流动损失，提升涡轮级做功能力，但同时会增加最大融合圆角半径位置处的流动损失；当静叶最大融合圆角相对半径和相对轴向弦长位置分别为0.16和0.47时，涡轮得到最佳的整体提升效果，此时等熵效率提高了0.010 %，比功率提升了0.141%。

To solve the flow loss caused by the secondary flow of the gas turbine in the end zone,the effectiveness of blended blade and end wall (BBEW) technique in turbine aerodynamic optimization was studied.Taking the first stage cascade of the E3 model highpressure turbine as the research object,different forms of BBEW modelings were performed on the lower end walls of the suction surface of the turbine stator vane,the total temperature and the total pressure of the inlet are set to 709 K and 344.74 kPa respectively,and the contribution of BBEW technique to the reduction of end wall aerodynamic loss and the improvement of turbine stage efficiency and doing work capability was studied by use of numerical calculation.The research results show that the application of BBEW technique can effectively reduce local flow loss in the end zone and improve the doing work capability of the turbine stage,but at the same time it will increase the flow loss at the position of the maximum fusion fillet radius.When the relative radius of the maximum fusion fillet of the stator vane is 0.16 and the relative axial chord length position is 0.47,the overall effect of turbine improvement is the best.At this time,the isentropic efficiency is increased by 0.010%,and the specific power is increased by 0.141%.

TK14

国家自然科学基金（52071107）；国家科技重大专项（J2019-Ⅱ-0009-0029）