Aeroelastic Analysis of a Transonic Fan Blade with Low Hub-to-Tip Ratio including Mistuning Effects

Zhizhong Fu, Yanrong Wang

School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China.

DOI: 10.4236/jpee.2015.34049                

Abstract

This paper presents a comprehensive investigation of aeroelastic stability for a high aft-swept transonic fan blade with low hub-to-tip ratio. The evolution of the blade’s aeroelastic stability in the first bending modes is studied. A 3D flutter computation representing today’s industry standard is performed. Steady state flow field and motion-induced unsteady pressures acting on the blade have been determined by a 3D Reynolds-Averaged Navier-Stokes (RANS) equations with a standard k-ε turbulence model. A weakly coupled (one-way) method has been employed to describe the interaction between fluid and structure. The results of aerodynamic damping indicate a significant shock-driven risk. To increase the flutter margin by a viable method, a statistical mistuned aeroelastic stability investigation has been performed. It has been found that alternately intentional mistuning with a small blade frequency offset stabilizes the system effectively. However, as the standard deviation of random mistuning reaches some critical values, the introduction of alternately intentional mistuning does not provide any additional stabilizing effects.

Keywords

Aeroelastic Stability, Flutter, Turbomachinery, Mistuning

Conflicts of Interest

The authors declare no conflicts of interest.

References

[1]	Groth, P., M?rtensson, H. and Andersson, C. (2010) Design and Experimental Verification of Mistuning of a Supersonic Turbine Blisk. Journal of Turbomachinery, 132, Article ID: 011012. http://dx.doi.org/10.1115/1.3072492
[2]	Zhai, Y., Bladh, R. and Dyverfeldt, G. (2012) Aeroelastic Stability Assessment of an Industrial Compressor Blade including Mistuning Effects. Journal of Turbomachinery, 134, Article ID: 060903. http://dx.doi.org/10.1115/1.4007210
[3]	Zhang, X.W., Wang, Y.R. and Xu, K.N. (2011) Flutter Prediction in Turbomachinery with Energy Method. Proc IMechE Part G. Journal of Aerospace Engineering, 225, 995-1002.
[4]	Hsu, K. and Hoyniak, D. (2011) A Fast Influence Coefficient Method for Linearized Flutter and Forced Response Analysis. 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, 4-7 January 2011, 1-11. http://dx.doi.org/10.2514/6.2011-229
[5]	Huang, X.Q., He, L. and Bell, D.L. (2009) Experimental and Computational Study of Oscillating Turbine Cascade and Influence of Part-Span Shrouds. Journal of Fluids Engineering, 131, Article ID: 051102. http://dx.doi.org/10.1115/1.3111254
[6]	Hall, K.C., Kielb, R.E., Ekici, K., et al. (2005) Recent Advancements in Turbomachinery Aeroelastic Design Analysis. 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, 10-13 January 2005, 1-23. http://dx.doi.org/10.2514/6.2005-14
[7]	Kenyon, J.A. and Griffin, J.H. (2003) Experimental Demonstration of Maximum Mistuned Bladed Disk Forced Response. Journal of Turbomachinery, 125, 673-681. http://dx.doi.org/10.1115/1.1624847
[8]	Lim, S.H., Bladh, R. and Castanier, M.P. (2007) Compact, Generalized Component Mode Mistuning Representation for Modeling Bladed Disk Vibration. AIAA Journal, 45, 2285-2298. http://dx.doi.org/10.2514/1.13172
[9]	Petrov, E.P. (2011) Reduction of Forced Response Levels for Bladed Disks by Mistuning: Overview of the Phenomenon. Journal of Engineering for Gas Turbines and Power, 133, Article ID: 072501. http://dx.doi.org/10.1115/1.4002619
[10]	Carta, F.O. (1967) Coupled Blade-Disk-Shroud Flutter Instabilities in Turbojet Engine Rotors. Journal of Engineering for Gas Turbines and Power, 89, 419-426. http://dx.doi.org/10.1115/1.3616708
[11]	Sanders, A.J., Hassan, K.K. and Rabe, D.C. (2004) Experimental and Numerical Study of Stall Flutter in a Transonic Low-Aspect Ratio Fan Blisk. Journal of Turbomachinery, 126, 166-174. http://dx.doi.org/10.1115/1.1645532
[12]	Bakhle, M.A., Thomas, J.P. and Reddy, T.S.R. (2008) Fan Flutter Computations Using the Harmonic Balance Method. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Hartford, 21-23 July 2008, 1-7. http://dx.doi.org/10.2514/6.2008-4743
[13]	Vasanthakumar, P. (2011) Computation of Aerodynamic Damping for Flutter Analysis of a Transonic Fan. Proceedings of ASME Turbo Expo 2011, GT2011, Vancouver, 6-10 June 2011, 1-9. http://dx.doi.org/10.1115/GT2011-46597
[14]	McBean, I., Hourigan, K., Thompson, M., et al. (2005) Prediction of Flutter of Turbine Blades in a Transonic Annular Cascade. Journal of Fluids Engineering, 127, 1053-1058. http://dx.doi.org/10.1115/1.2060731
[15]	Choi, Y.S., Gottfried, D.A. and Fleeter, S. (2010) Resonant Response of Mistuned Bladed Disks including Aerodynamic Damping Effects. Journal of Propulsion and Power, 26, 16-24. http://dx.doi.org/10.2514/1.36537
[16]	Choi, Y.S., Lawless, P.B. and Fleeter, S. (2007) An Investigation of the Reso-nant Response of Mistuned IBRs. 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 8-11 July 2007, 1-13. http://dx.doi.org/10.2514/6.2007-5036
[17]	Avalos, J. and Mignolet, M.P. (2010) Maximum Amplification of Blade Response in Mistuned Multi Stage Assemblies. Proceedings of ASME Turbo Expo 2010: Power for Land, Sea and Air, GT2010, Glasgow, 14-18 June 2010, 1-14. http://dx.doi.org/10.1115/GT2010-23062
[18]	Groth, P., M?rtensson, H. and Andersson, C. (2010) Design and Experimental Verification of Mistuning of a Supersonic Turbine Blisk. Journal of Turbomachinery, 132, Article ID: 011012. http://dx.doi.org/10.1115/1.3072492
[19]	Martel, C., Corral, R. and Llorens, J.M. (2008) Stability Increase of Aero-dynamically Unstable Rotors Using Intentional Mistuning. Journal of Turbomachinery, 130, Article ID: 011006. http://dx.doi.org/10.1115/1.2720503
[20]	Mayorca, M.A., Vogt, D.M., M?rtensson, H., et al. (2012) A New Reduced Order Modeling for Stability and Forced Response Analysis of Aero-Coupled Blades Considering Various Mode Families. Journal of Turbomachinery, 134, Article ID: 051008. http://dx.doi.org/10.1115/1.4003830