Skip to main content
SpringerLink
Log in

The Investigation of Rotating Instability Under Distortion Based on a Compressor Rotor

  • Original Paper
  • Published:
International Journal of Aeronautical and Space Sciences Aims and scope Submit manuscript

Abstract

The twisted-swept fan is one of the most important components of a high bypass ratio engine. Under clean inlet flow or inlet distortion, the unsteady flow field of the fan rotor near stall condition is obtained by numerical simulation. At the same time, fast Fourier transform (FFT) transformation of the monitors is completed. Fans with different tip clearances are compared and analyzed under intake distortion conditions. Different types of total circumferential pressure distortion are also compared and analyzed. Under inlet distortion, modal analysis of the unsteady flow field was performed using dynamic mode decomposition (DMD) method. The reduced-order decomposition of flow field effectively analyzes structures of flow field under distorted conditions. Finally, Fast Fourier Transform and circumferential mode are applied to inlet distortion flow field of the fan rotor. Rotating instability phenomenon was found in distortion conditions. When inlet flow is clean, there is no rotating instability phenomenon. This shows intake air can cause rotating instability (RI) phenomenon of the flow field under distortion. This provides a new explanation for rotating instability phenomenon different from existing research. The effective application of two analysis methods provides new analysis ideas for the unstable flow field.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15
Fig. 16
Fig. 17
Fig. 18
Fig. 19
Fig. 20
Fig. 21
Fig. 22
Fig. 23
Fig. 24
Fig. 25
Fig. 26
Fig. 27
Fig. 28
Fig. 29
Fig. 30
Fig. 31
Fig. 32
Fig. 33

Similar content being viewed by others

References

  1. Day IJ (2016) Stall, surge, and 75 years of research. J Turbomach 138(1):011001

    Article  Google Scholar 

  2. Zhang W, Stapelfeldt S, Vahdati M (2020) Influence of the inlet distortion on fan stall margin at different rotational speeds. Aerosp Sci Technol 98:105668

    Article  Google Scholar 

  3. Murphy JP, MacManus DG (2010) Inlet ground vortex aerodynamics under headwind conditions. Aerosp Sci Technol 15(3):207–215

    Article  Google Scholar 

  4. Dong X, Sun D, Li F, Sun X (2017) Stall margin enhancement of a novel casing treatment subjected to circumferential pressure distortion. Aerosp Sci Technol 73:239–255

    Article  Google Scholar 

  5. Tan CS, Day I, Morris S et al (2010) Spike-type compressor stall inception, detection, and control. Annu Rev Fluid Mech 42(1):275–300

    Article  Google Scholar 

  6. Yao J, Cargill PL, Holmes DG, SE (2010) Aspects of numerical analysis for unsteady flows in aircraft engines, AIAA paper 2010-1603

  7. Iseler J, Niehuis R (2008) Steady and unsteady flow-simulation of an axial transonic compressor stage, AIAA paper 2008-83

  8. Hongwei M, Haokang J (2000) Three-dimensional mean flow field at both inlet and exit of an isolated axial compressor rotor passage in different conditions. J Aerosp Power 15(2):119–123

    Google Scholar 

  9. Hongwei M, Haokang J (2001) Three-dimensional mean flow field at both inlet and exit of an isolated axial compressor rotor passage at a near stall condition. J Eng Thermophys 22(06):700–702

    Google Scholar 

  10. Bennett LGN, Allan WDE (2009) Examination of rotating stall inception in a small high speed axial compressor, ASME Paper, GT2009-59420

  11. Zheng X, Sun Z, Kawakubo T, Tamaki H (2018) Stability improvement of a turbocharger centrifugal compressor by non-axisymmetric vaned diffuser. J Turbomach Trans ASME 140(4):041007-1-041007–13

    Article  Google Scholar 

  12. Mathioudakis K, Breugelmans FAE (1985) Development of small rotating stall in a single stage axial compressor. In: ASME 1985 international gas turbine conference and exhibit. american society of mechanical engineers, p V001T03A064

  13. Kameier F, Neise W (1997) Rotating blade flow instability as a source of noise in axial turbomachines. J Sound Vib 203(5):833–853

    Article  Google Scholar 

  14. Vo HD (2010) Role of tip clearance flow in rotating instabilities and nonsynchronous vibrations. J Propul Power 26:556–561

    Article  Google Scholar 

  15. Zhang K, Wang AJ (2020) Analysis of near stall condition of high bypass fan rotor based on airworthiness certification. Aerosp Sci Technol 99:105733

    Article  Google Scholar 

  16. Schmid PJ (2011) Application of the dynamic mode decomposition to experimental data. Exp Fluids 50(4):1123–1130

    Article  Google Scholar 

  17. Schmid PJ (2010) Dynamic mode decomposition of numerical and experimental data. J Fluid Mech 656:5–28

    Article  MathSciNet  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Shanghai Jiao Tong University, Shanghai, China

    K. Zhang

  2. Pusan National University, Busan, South Korea

    W. G. Park

Authors
  1. K. Zhang
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. W. G. Park
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to K. Zhang.

Additional information

Publisher's Note

Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Zhang, K., Park, W.G. The Investigation of Rotating Instability Under Distortion Based on a Compressor Rotor. Int. J. Aeronaut. Space Sci. 23, 471–483 (2022). https://doi.org/10.1007/s42405-022-00467-2

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s42405-022-00467-2

Keywords

Search

Navigation