总 温 畸 变 下 跨 声 压 气 机 失 速 过 程 非 定 常 模 拟

To investigate the stall mechanism of a transonic compressor with inlet total temperature distortion，full an⁃ nular unsteady numerical simulations with a 500 K，180° circumferential total temperature distortion are conducted on the German Darmstadt transonic compressor. The results indicate that the mass flow rate and the total pressure ratio decrease dramatically under the inlet total temperature distortion. The total pressure radial distribution varies at differ⁃ ent circumferential positions on the compressor rotor exit. Along the rotor rotating direction，the total pressure gradually decreases in the high temperature region，and gradually increases in the low temperature region. The closer to the stall point，the greater non-uniform of the total pressure radial distribution. As the mass flow is further reduced，the type of the inception induced stall is spike，appearing first when the rotor blades turn into the high total temperature re⁃ gion. The circumferential propagation speed of the stall inception and that of the stall cells at the beginning of the stall are about 88. 9% and 66. 0% of the rotor speed，respectively. The entire stall process is accompanied by a significant fluctuation of the mass flow，caused by the movement and merging of the stall cells along the circumferential direction.