Skip to main content

Stall Margin Enhancement of Aeroengine Compressor with a Novel Type of Alternately Swept Blades

  • Conference paper
  • First Online:
Proceedings of the International Conference on Aerospace System Science and Engineering 2019 (ICASSE 2019)

Part of the book series: Lecture Notes in Electrical Engineering ((LNEE,volume 622))

Included in the following conference series:

  • 837 Accesses

Abstract

Rotating stall, as a typical kind of flow instability in aero-compressor, could lead to disastrous consequences of aeroengine. Therefore, an effective method is perused to enhance the stall margin. Some of the previous researches focus on the holistically swept rotor. This paper concentrates on the impact of a novel type of axial swept blades on the aerodynamic behaviour of transonic axial-flow compressor rotors. A CFD package, which solves the Reynolds-averaged Navier–Stokes equations, is used to compute the complex flow field of the compressor. It is validated against the existing experimental data. Comparisons with experimental data indicate that the overall features of the rotor performance are calculated well by the numerical solution with acceptable accuracy. A number of new swept rotors were modelled based on the original blade, by axially moving the location of blade alternately. All the new rotors are simulated, and comparison of the results shows that the alternately swept rotor enhances the stall margin effectively. The stall margin of new rotors can reach up to 18.16%, while that of the original rotor is only 9.71%. More physical explanations on the stall margin improvement are given based on a detailed analysis of the flow field.

Although this paper is partly inspired by the reference [15] and [18], the substance and the methods are different between this paper and these two references.

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

Access this chapter

Chapter
USD 29.95
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
eBook
USD 129.00
Price excludes VAT (USA)
  • Available as EPUB and PDF
  • Read on any device
  • Instant download
  • Own it forever
Softcover Book
USD 169.99
Price excludes VAT (USA)
  • Compact, lightweight edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info
Hardcover Book
USD 169.99
Price excludes VAT (USA)
  • Durable hardcover edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info

Tax calculation will be finalised at checkout

Purchases are for personal use only

Institutional subscriptions

Similar content being viewed by others

References

  1. Kai Z (2008) The investigation of the tip clearance flow of axial flow compressor with adjustable tip additional blades. Harbin Institute of Technology, Harbin

    Google Scholar 

  2. Paduano J, Epstein AH, Valavani L, Longley JP, Greitzer EM, Guenette GR (1991, June) Active control of rotating stall in a low speed axial compressor. In: ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, pp V001T01A036–V001T01A036

    Google Scholar 

  3. Day IJ (1991, June). Stall inception in axial flow compressors. In: ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, pp V001T01A034–V001T01A034

    Google Scholar 

  4. Houghton T, Day I (2011) Enhancing the stability of subsonic compressors using casing grooves. J Turbomach 133(2):021007

    Article  Google Scholar 

  5. Rukavina J, Okiishi T, Wennerstrom A (1990) Stall margin improvement in axial-flow compressors by circumferential variation of stationary blade setting angles. In: 26th joint propulsion conference, p 1912

    Google Scholar 

  6. Vo HD, Tan CS, Greitzer EM (2008) Criteria for spike initiated rotating stall. J Turbomach 130(1):011023

    Article  Google Scholar 

  7. Pullan G, Young AM, Day IJ, Greitzer EM, Spakovszky ZS (2015) Origins and structure of spike-type rotating stall. J Turbomach 137(5):051007

    Article  Google Scholar 

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

    Article  ADS  Google Scholar 

  9. Ahn CS, Kim KY (2002) Aerodynamic design optimization of an axial compressor rotor. ASME Paper GT-2002-30445

    Google Scholar 

  10. Denton JD, Xu L (1998) The exploitation of three-dimensional flow in turbomachinery design. Proc Inst Mech Eng Part C: J Mech Eng Sci 213(2):125–137

    Article  Google Scholar 

  11. Yamaguchi N (1991) Secondary-loss reduction by forward-skewing of axial compressor rotor blading. 91-YOKOHAMA 8

    Google Scholar 

  12. Hah C, Puterbaugh SL, Wadia AR (1998, June) Control of shock structure and secondary flow field inside transonic compressor rotors through aerodynamic sweep. In: ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, pp V001T01A132–V001T01A132

    Google Scholar 

  13. Wadia AR, Szucs PN, Crall DW (1997, June) Inner workings of aerodynamic sweep. In: ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, pp V001T03A062–V001T03A062

    Google Scholar 

  14. Denton JD, Xu L (2002, January) The effects of lean and sweep on transonic fan performance. In: ASME Turbo Expo 2002: Power for Land, Sea, and Air. American Society of Mechanical Engineers, pp 23–32

    Google Scholar 

  15. He C, Ma Y, Liu X, Sun D, Sun X (2018) Aerodynamic instabilities of swept airfoil design in transonic axial-flow compressors. AIAA J 1878–1893

    Google Scholar 

  16. Moore RD, Reid L (1980) Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05. NASA-TP-1659, E-138

    Google Scholar 

  17. Benini E, Biollo R (2006, January) On the aerodynamics of swept and leaned transonic compressor rotors. In: ASME Turbo Expo 2006: Power for Land, Sea, and Air. American Society of Mechanical Engineers, pp 283–291

    Google Scholar 

  18. He C, Sun D, Sun X (2018) Stall inception analysis of transonic compressors with chordwise and axial sweep. J Turbomach 140(4):041009

    Article  Google Scholar 

  19. Dunham J (1998) CFD validation for propulsion system components (la validation CFD des organes des propulseurs) (No. AGARD-AR-355). Advisory Group for Aerospace Research and Development Neuilly-Sur-Seine (France)

    Google Scholar 

  20. Allmaras SR, Johnson FT (2012, July) Modifications and clarifications for the implementation of the Spalart-Allmaras turbulence model. In: Seventh International Conference on Computational Fluid Dynamics (ICCFD7), pp 1–11

    Google Scholar 

Download references

Acknowledgements

The first author greatly appreciates the support from China Scholarship Council. This work is also supported by Natural Science Foundation of China (No. 51576124, No. 51506126). The support from the United Innovation Centre (UIC) of Aerothermal Technologies for Turbomachinery is also acknowledged.

Author information

Authors and Affiliations

Authors

Corresponding author

Correspondence to Xiaohua Liu .

Editor information

Editors and Affiliations

Rights and permissions

Reprints and permissions

Copyright information

© 2020 Springer Nature Singapore Pte Ltd.

About this paper

Check for updates. Verify currency and authenticity via CrossMark

Cite this paper

Fang, C., Zhang, Y., Li, Y., Liu, X. (2020). Stall Margin Enhancement of Aeroengine Compressor with a Novel Type of Alternately Swept Blades. In: Jing, Z. (eds) Proceedings of the International Conference on Aerospace System Science and Engineering 2019. ICASSE 2019. Lecture Notes in Electrical Engineering, vol 622. Springer, Singapore. https://doi.org/10.1007/978-981-15-1773-0_4

Download citation

Publish with us

Policies and ethics