针对燃气轮机启动阶段压气机旋转失速及喘振问题突出的现象，对某燃气轮机压气机部件的启动过程进行了数值模拟，并比较了不同升转速率及进口可调导叶角度的升转过程中，速度云图、沿叶高总压分布等相关参数。模拟结果显示：不同的升转速率对于叶高较低位置流场的影响不大，但是在0.9叶高处会存在明显差异，2 r/s2升转速率下，动叶尾缘流动分离较弱，4 r/s2升转速率下，低速区基本占据流道空间；动叶叶片尖端的流动分离现象在进口可调导叶逆时针旋转5°时，较其他工况得到明显抑制；进口可调导叶角度的变化带来流场改变的同时，在叶顶间隙会出现一个沿着压力侧的高速区。

In response to the prominent issues of compressor stall and surge during the startup stage of a gas turbine, numerical simulations were conducted on the startup process of a certain gas turbine compressor component, and relevant parameters such as velocity cloud maps and total pressure distribution along blade height were compared during the startup process at different acceleration rates and inlet guide vane (IGV) angles. The simulation results show that different acceleration rates have little effect on the flow field at lower blade heights, but there is a significant difference at 0.9 blade height. Among them, at 2 r/s2 acceleration rate, there is a smaller flow separation at the trailing edge of moving blade, while at 4 r/s2 acceleration rate, lowspeed zone basically occupies the flow channel space; the flow separation phenomenon at the tip of the moving blade is significantly suppressed when the IGV rotates counterclockwise by 5° compared to that under other operating conditions; the change in IGV angle brings about changes in the flow field, and at the same time, a highspeed zone along the pressure side will appear in the blade tip gap.

TK221