采用数值求解三维URANS方程和SST湍流模型的方法,研究了导叶尾缘下端壁造型对轮缘密封的封严性能及涡轮主流气动性能的影响。对比了导叶尾缘5种不同端壁造型结构的轮缘密封封严效率和涡轮级效率。结果表明,导叶尾缘端壁凹凸幅值较大时会降低涡轮级效率,凹陷端壁降低0.377%,凸起端壁降低0.103%。导叶尾缘端壁造型会影响转静间隙附近的流动形态,进而影响轮缘密封封严效率。凸起端壁使转静间隙附近的主流径向分速度减小,燃气入侵增加,MFR=0.3%时,较无端壁造型封严效率降低0.13；凹陷端壁使转静间隙附近的主流径向分速度增大,燃气入侵减少,MFR=0.3%时,较无端壁造型封严效率提升0.2。

The effect of endwall profiling of vane trailing edge on sealing effectiveness of rim seal is numerically investigated using 3D Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations and SST turbulent model. The sealing effectiveness of rim seal and aerodynamic performance of turbine stage are compared among five kinds of endwall profiling of vane trailing edge. The numerical results show that the turbine stage efficiency is reduced by 0.377% for the concave endwall and 0.103% for the convex endwall when the amplitude is large. The endwall profiling of vane trailing edge affects the sealing effectiveness of rim seal by changing the flow pattern near the stator-rotor clearance. The convex endwall reduces the radial component velocity of main flow, resulting in increased gas ingestion. When MFR=0.3%, the sealing effectiveness is 0.13 lower than that of the axisymmetric endwall. The concave endwall increases the radial component velocity of main flow, resulting in reduced the gas ingestion. When MFR=0.3%, the zsealing effectiveness is 0.2 higher than that of the axisymmetric endwall.

TK474.7；

国家自然科学基金(52006178,U2241268),国家科技重大专项(2022-DC-I-002-001),国家自然科学基金项目（面上项目，重点项目，重大项目）