喘振现象是压气机部件较为常见的故障之一，工程中经常采用可调静子叶片调节机构改变角度进而预防喘振现象的发生。为明确可调静子叶片调节机构的运行特性，满足可调静子叶片调节机构在运行过程中运行特性要求，依托某型航空发动机设计搭建了VSV机构运动特性试验台，开展了在不同速度下VSV机构阻力的专项验证试验，分别得到了不同配合间隙衬套工况下叶片转动角度数据、不同速度工况下调节机构阻力数据。试验结果表明：叶片角度下降行程中变化曲线波动较上升行程更大，叶片级数越高，转动角度范围越小，S0、S4级叶片转动角度分别保持在30°与3°附近。并且在回程阶段驱动力幅值减小且保持较为平稳状态，同时在作动筒驱动上升及下降行程下存在着阶跃现象，S1级下降行程阶跃现象表现更明显，上升行程为约-400 N，而下降行程可达-450 N。试验结果对航空发动机VSV调节机构运行特性的研究具备着一定的参考意义及价值。

Surge phenomenon is one of the common faults in compressor components. The adjusting mechanism of variable stator vane is of-ten used to change the angle and prevent the occurrence of surge phenomenon in engineering. To determine the operating characteristics of the adjusting mechanism of variable stator vane and meet the operating requirements in the operating process, a test rig for the operating characteristics of the VSV mechanism was designed and built based on a certain type of aero-engine. A dedicated resistive force of the VSV mechanism at different speeds verification test of was carried out, and the blade rotation angle data under different tolerance clearance bushing conditions and the mechanism resistance data under different speeds conditions were obtained. The test results show that the fluctuation of the blade angle in descending stroke is larger than which in ascending stroke, and the higher number of blade stages, the smaller the range of the rotation angle is, and the rotation angle of the S0 and S4 stage blades is kept near 30° and 3°, respectively. And the amplitude of driving force decreases and remains relatively stable in return stage. The step phenomenon occurs during the ascending and descending strokes of the actuator cylinder. the step phenomenon of S1 stage in descending stroke is more obvious, the up stroke is about -400 N, and the down stroke can reach -450 N. The test results have certain reference significance and value for the study of the operating characteristics of the aero-engine VSV adjusting mechanism.