Volume 39 Issue 6
Jun.  2024
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WANG Lei, GAO Limin, MAO Xiaochen, et al. Effect of slot casing treatment on first stall stage of counter-rotating compressor[J]. Journal of Aerospace Power, 2024, 39(6):20220392 doi: 10.13224/j.cnki.jasp.20220392
Citation: WANG Lei, GAO Limin, MAO Xiaochen, et al. Effect of slot casing treatment on first stall stage of counter-rotating compressor[J]. Journal of Aerospace Power, 2024, 39(6):20220392 doi: 10.13224/j.cnki.jasp.20220392

Effect of slot casing treatment on first stall stage of counter-rotating compressor

doi: 10.13224/j.cnki.jasp.20220392
  • Received Date: 2022-06-01
    Available Online: 2023-12-25
  • In order to explore the influence of slot casing treatment on the first stall stage of counter-rotating compressor, a two-stage counter-rotating compressor was taken as the research object. The influence of slot casing treatment on the first stall stage of the counter-rotating compressor was studied by numerical simulation method. The results showed that the slot casing treatment did not change the initial stall disturbance type of the counter-rotating compressor, which was still a spike stall. The first stall stage of the compressor was converted from rotor R2 to rotor R1 by the forward movement of the casing treatment, while the backward movement of the casing treatment did not change the stall stage of the compressor. After casing treatment, the leading edge spillage of the rotor R2 was inhibited, and the unsteady fluctuation intensity in the blade passage was reduced. However, the leading edge spillage of the rotor R1 was intensified under the near-stall condition. The interface between the mainstream and the leakage flow was pushed out of the blade passage. At the same time, the unsteady oscillation intensity in the blade passage was increased, which finally made the rotor R1 first enter the stall state. It was difficult to suppress the occurrence of leading edge spillage when the casing treatment was processed to move downstream of rotor R2. Although the leading edge spillage phenomenon also occurred at rotor R1 at this time, the leading edge spillage of rotor R2 was more intensified, and the position of the interface of the mainstream and leakage flow was further away from the leading edge of the blade, making it easier for the compressor to stall.

     

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