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 com-pressor component,and relevant parameters such as velocity cloud maps and total pressure distribution a-long 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/s2 acceleration rate,there is a smaller flow separation at the trailing edge of moving blade,while at 4 r/s2 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 counterclock-wise by 5 ° compared to that under other operating conditions;the change in IGV angle brings about chan-ges in the flow field,and at the same time,a high-speed zone along the pressure side will appear in the blade tip gap.
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