为解决某燃气轮机试验中频繁出现转子轴向力调整困难的问题，基于一种转-静盘腔气动轴向推力的直接动态测试方法，通过对比实验揭示轮缘密封半径、轴端密封结构及卸荷孔对转-静盘腔气动轴向力的影响规律。结果表明：轴端迷宫密封半径从22mm增大到42mm，轮盘轴向力减少约74.1%；与直梳齿相比，当轴端迷宫密封齿具有5°的倾角时，轴向力减少约71.1%；轴端迷宫密封的间隙比从1.14%增加到1.82%时，轴向力减少约87.7%；此外，周向布置卸荷孔也可以降低气动轴向推力约50.3%。当燃气轮机转子轴向力失衡时，可通过调整迷宫密封半径、倾角、间隙比与增加卸荷孔等方式，实现转子轴向力调整。

In order to solve the problem of difficult adjustment of rotor axial force in a gas turbine test, based on a direct dynamic test method for aerodynamic axial thrust of rotor-stator cavity, the influence of rim seal radius, shaft end seal structure and unloading hole on the aerodynamic axial force of rotor-stator cavity was revealed by comparative experiments. The results show that the axial force of the disc decreases by about 74.1% when the radius of the shaft end labyrinth seal increases from 22 mm to 42 mm. Compared with the straight comb tooth, when the shaft end labyrinth seal tooth has a 5° inclination angle, the axial force is reduced by about 71.1%. When the clearance ratio of the shaft end labyrinth seal increases from 1.14% to 1.82%, the axial force decreases by about 87.7%. In addition, the circumferential arrangement of unloading holes can also reduce the aerodynamic axial thrust by about 50.3%. When the axial force of the gas turbine rotor is unbalanced, the axial force of the rotor can be adjusted by adjusting the labyrinth seal radius, inclination angle, clearance ratio and increasing the unloading hole.

国家自然科学基金项目(52305176)；黑龙江省自然科学基金联合引导项目(JJ2020LH1197)；中央高校基本科研经费(JD2423)