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The Mechanism Analysis of Rotor/Rotor Interference Phenomenon within the Multistage Transonic Compressor

  • S.I.: Computations & Experiments on Dynamics of Complex Fluid & Structure
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Abstract

With the development of the load level of the multistage axial compressor, the interaction among different rotors, which usually keeps at high intensity and significantly influences the compressor performance, should not be ignored during the compressor design. The research aims to reveal the mechanisms of an interaction phenomenon between R1 (the first rotor) and R2 (the second rotor) in which the blade sweep characteristics are influenced by multiple factors such as the shock wave and wake flow effects. Unlike the traditional explanation, the results present the essence of a special R1-2BPF (the second harmonic of the blade passing frequency of R1) disturbance originating from R1 which is different from the commonly-recognized harmonic of blade wake effect and generated by the interaction between the oblique shock wave at R1 leading-edge and the pressure rise region after the passage shock wave. It is the coupling effect of this structure, wake separation region of R1 and S1, and the suction-side flow separation of R2 that determines the propagation of R1-1BPF (the first harmonic of the blade passing frequency of R1) and R1-2BPF disturbances inside the rotor passages. Moreover, under the additional impacts of the R2 hub slope and centrifugal force, it is noticed that the strengths of the R1-1BPF and R1-2BPF disturbances suddenly increase at some specific locations. All the results will provide more theories to the optimization of highly loaded compressor.

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Data Availability

All data, models, and code generated or used during the study appear in the submitted article.

Abbreviations

BPF:

blade passing frequency

c r :

the radial velocity

c u :

the circumferential velocity

f r :

the radial force in source term

LE:

leading edge

p rot2 :

pressure rise within R2

ps :

pressure rise from inlet

p ′ :

the assemble-average pressure distrubance at specific phase

\(\overset{\sim }{\mathrm{p}}\) :

pressure coefficient

R1:

the first rotor

R1-1BPF:

the disturbance of R1 at blade passing frequency

R1-2BPF:

the disturbance of R1 at the second harmonic of blade passing frequency

R2:

the second rotor

S1:

the first stator

TE:

trailing edge

u tip :

tip tangential speed of R1

ρ:

the density of air

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Acknowledgements

The authors would like to gratefully acknowledge the support of National Natural Science Foundation of China (No. 52130603 and 11732016).

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Authors and Affiliations

  1. High Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang, 622761, China

    J. Zhao & D. Yang

  2. Institute of Aeronautics and Astronautics, Xihua University, Chengdu, China

    Q. Lu

  3. AECC Sichuan Gas Turbine Research Institute, Chengdu, China

    H. Xiang

Authors
  1. J. Zhao
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  2. Q. Lu
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  3. D. Yang
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  4. H. Xiang
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Correspondence to J. Zhao.

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Zhao, J., Lu, Q., Yang, D. et al. The Mechanism Analysis of Rotor/Rotor Interference Phenomenon within the Multistage Transonic Compressor. Exp Tech 47, 295–312 (2023). https://doi.org/10.1007/s40799-022-00545-w

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  • DOI: https://doi.org/10.1007/s40799-022-00545-w

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