Skip to main content

Dynamic Response of a High Speed Flexible Rotor Due to Sudden Large Unbalance

  • Conference paper
  • First Online:
Proceedings of the 9th IFToMM International Conference on Rotor Dynamics

Part of the book series: Mechanisms and Machine Science ((Mechan. Machine Science,volume 21))

Abstract

Structure vibration response of rotor-bearing-case-installation section system caused by sudden unbalance load due to blade out of the high-speed flexible rotor has been the focus in the field of aero-engine development. This paper deals with the sudden unbalance response characteristics of a high-speed flexible rotor during a blade out event. To reveal the unbalance response influence of blade released mass and rotating speed, a flexible rotor-damping support-protection support system is constructed using LS-DYNA. This model consists of rotor, disk, single blade, protection support and damping support. The diameter of the disk is designed to be 196 mm and the mass of a released blade is 33 or 66 g with two different widths. It can be seen from the shearing stress results that the rotor shaft is twisted off at a weak key point. After single blade out, rubbing between rotor and protection support is classified as the following two stages. It is observed that as single blade released out, higher rotating speed and larger unbalance mass lead to more violent vibration and cause more severe impact force transmitted to bearing and installation section. They can also lead to less stay time during the first stage mentioned above. To verify the results of simulation, blade out tests are carried out on a high speed spin tester. Severe vibration happens on the support base in the course of shutting down, but rotor has no apparent damage in single blade out test with small mass and low speed. However single blade out event with larger mass and higher speed can cause more danger. Large and long-term unbalance on protection support-support base-protection ring-hanger makes the system vibrate severely and these can lead to break of the support base and twist of the rotor shaft. It can be concluded that the results of tests turn out to be agreed well with those of simulation analysis.

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 259.00
Price excludes VAT (USA)
  • Available as EPUB and PDF
  • Read on any device
  • Instant download
  • Own it forever
Softcover Book
USD 329.99
Price excludes VAT (USA)
  • Compact, lightweight edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info
Hardcover Book
USD 329.99
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. Xuan H, Lu X, Hong W (2010) Review of aero-engine case containment research. J Aerosp Power 25:1860 (in Chinese)

    Google Scholar 

  2. Chen G (2006) Analysis of aeroengine structure design. Beijing University of Aeronautics and Astronautics Press, Beijing (in Chinese)

    Google Scholar 

  3. Sinha SK, Dorbala S (2009) Dynamic loads in the fan containment structure of a turbofan engine. J Aerosp Eng 22:260

    Article  Google Scholar 

  4. Stallone J, Gallardo V, Storace AF et al (1983) Blade loss transient dynamic analysis of turbomachinery. AIAA J 21(8):1134–1138

    Article  Google Scholar 

  5. Lesaffre N, Sinou JJ, Thouverez F (2007) Contact analysis of a flexible bladed-rotor. Eur J Mech A Solids 26:541

    Article  MATH  Google Scholar 

  6. U.S. Department of Transportation, Federal Aviation Administration (1984) Federal aviation regulations, Part 33, AirWorthiness Standards, Aircraft Engines

    Google Scholar 

  7. Cosme N, Chevrolet D, Bonini J et al (2002) Prediction of engine loads and damages due to fan blade off event. In: 43rd AIAA/ASME/ASCE/AHS/ASC structures, structural dynamics, and materials conference, Denver

    Google Scholar 

  8. Cosme N, Chevrolet D, Bonini J (2002) Prediction of transient engine loads and damage dueto hollow fan blade-off. Revue Européenne des Eléments 11:651

    Article  MATH  Google Scholar 

  9. Lawrence C, Carney K, Gallardo V (2001) Simulation of aircraft engine blade-out structural dynamics. NASA/TM-2001-210957/REV1, RECON, 2001.1556. Applied materials and technologies for modern manufacturing

    Google Scholar 

  10. Carney v, Lawrence C, Carney DV (2002) Aircraft engine blade-out dynamics. In: Seventh international LS-DYNA users conference, Livermore CA, USA, pp 14–17

    Google Scholar 

  11. Lawrence C, Carney K, Gallardo VA (2003) A study of fan stage/casing interaction models. In: NASA/TM-2003-212215, NASA Glenn Research Center, Washington, DC

    Google Scholar 

  12. Ortiz R, Herran M, Chalons H (2009) Blade loss studies in low-pressure turbines–from blade containment to controlled blade-shedding. Comput Methods Exp Meas. doi: 10.2495/CMEM090501

Download references

Author information

Authors and Affiliations

Authors

Corresponding author

Correspondence to Xuan Haijun .

Editor information

Editors and Affiliations

Rights and permissions

Reprints and permissions

Copyright information

© 2015 Springer International Publishing Switzerland

About this paper

Cite this paper

Haijun, X., Ling, L., Xiaojun, G., Guoqiang, L. (2015). Dynamic Response of a High Speed Flexible Rotor Due to Sudden Large Unbalance. In: Pennacchi, P. (eds) Proceedings of the 9th IFToMM International Conference on Rotor Dynamics. Mechanisms and Machine Science, vol 21. Springer, Cham. https://doi.org/10.1007/978-3-319-06590-8_164

Download citation

  • DOI: https://doi.org/10.1007/978-3-319-06590-8_164

  • Published:

  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-06589-2

  • Online ISBN: 978-3-319-06590-8

  • eBook Packages: EngineeringEngineering (R0)

Publish with us

Policies and ethics