Volume 35 Issue 11
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LI Kangdi, DU Yunxiang, XU Zili. DMD analysis of compressor stall inception and rotor flow field ,under multiple conditions[J]. Journal of Aerospace Power, 2020, 35(11): 2413-2420. doi: 10.13224/j.cnki.jasp.2020.11.018
Citation: LI Kangdi, DU Yunxiang, XU Zili. DMD analysis of compressor stall inception and rotor flow field ,under multiple conditions[J]. Journal of Aerospace Power, 2020, 35(11): 2413-2420. doi: 10.13224/j.cnki.jasp.2020.11.018
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DMD analysis of compressor stall inception and rotor flow field ,under multiple conditions

doi: 10.13224/j.cnki.jasp.2020.11.018

  • State Key Laboratory for Strength and Vibration of Mechanical Structures,School of Aerospace Engineering,Xi’an Jiaotong University,Xi‘an 710049,China

  • Received Date: 2019-12-24
  • Publish Date: 2020-11-28
    Abstract
  • The unsteady flow field of a transonic axial compressor Rotor 37 was numerically simulated, and the modal information of fluid pressure and velocity were obtained by the dynamic modal decomposition method(DMD). The stability of the compressor under different working conditions was determined, the main characteristic structures of the flow field were captured, and the stall aura of the compressor was found by the modal cloud diagram. The results showed that, the near stall point and the plugging point had unstable modal orders; the maximum error between DMD frequency and pressure spectrum was 063%; with the rise of backpressure, the fluid mass in the two adjacent blades gradually moved to the leading edge of the blade, and its range was expanded; at the near stall point, with the mixing of main flow and reflux, a semi-ellipsoidal vortex was generated in the middle of the blade suction surface and the flow channel was blocked, which was the initial manifestation of a spike stall.

     

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