为研究进气总温畸变条件下跨音压气机失速机理，对德国Darmstadt跨音单级压气机开展进口周向范围180°，高温区500 K的总温畸变条件下全环非定常数值模拟研究。结果表明：进气总温畸变条件下，压气机流量显著减小，总压比大幅下降。压气机转子出口面不同周向位置的总压径向分布不同。顺转子叶片旋转方向，在高温区，总压逐渐减小；低总温区域的转子出口总压高于高总温区域。随着压气机逐渐接近失速点，总压径向分布不均匀性增大。当流量进一步减小后，总温畸变下诱发旋转失速的先兆波为突尖型，最先出现失速先兆的周向位置是转子叶片离开低温区，转入高温畸变区时。失速先兆的周向传播速度约为88.9%转子转速，失速初期失速团的周向传播速度约为66%转子转速。整个失速过程伴随着转子出口流量的大幅度波动，由失速团沿周向的运动和合并引起。

To investigate the stall mechanism of a transonic compressor with inlet total temperature distortion, full annular un-steady numerical simulations with a 500k, 180-degree 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 different 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, and it appears first when the rotor blades turn into the high total temperature region. The circumferential propagation speed of the stall inception is about 88.9% of rotor speed, and the circumferential propagation speed of the stall cells at the beginning of the stall is about 66% of rotor speed. 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.