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Journal of Thermal Science

, Volume 27, Issue 4, pp 364–372 | Cite as

Numerical Investigation on Aeroelastic Behavior of Composite Material Plate Excited by Pulsed Air Jet

  • Hairun Xie
  • Yadong Wu
  • Anjenq Wang
  • Hua Ouyang
Article
  • 58 Downloads

Abstract

Nowadays, carbon fiber composite material is becoming more and more popular in aero engine industry due to its high specific strength and stiffness. Laminate carbon fiber composite material is widely used to manufacture the high load wide chord fan blade, containment casing, etc. The aeroelastic behavior of composite product is critical for the optimization of the product design and manufacturing. In order to explore its aeroelastic property, this paper discusses the coupled simulation of aerodynamic excitation applied on laminate composite material plate. Mechanical behavior of composite material plate is different from that of isotropic material plate such as metal plate, because it is anisotropy and has relative high mechanical damping due to resin between plies. These plates to be studied are designed using 4 different layup configurations which follow the design methods for composite fan blade. The numerical simulation of force response analysis mainly uses single frequency mechanical force input to simulate the electromagnetic shakers or other actuators, which could transmit mechanical force to the test parts. Meanwhile, pulsed air excitation is another way to “shake” the test parts. This excitation method induces aero damping into the test part and simulates the unsteady flow in aero engine, which could cause aeroelastic problems, such as flutter, forced response and non-synchronous vibration (NSV). In this study, numerical simulation using coupled method is conducted to explore the characteristics of laminate composite plates and the property of aerodynamic excitation force generated by pulsed air jet device. Modal analysis of composite plate shows that different ply stacking sequences have a significant impact on the plate vibration characteristics. Air pulse frequency and amplitude in flow field analysis are calibrated by hot wire anemometer results. As the air pulse frequency and amplitude are varied, incident angle of flow and layup configurations of plate can be analyzed in details by the simulations. Through the comparisons of all these factors, air pulse excitation property and the aeroelastic behavior of composite material plate are estimated. It would provide a possible way to guide the next-step experimental work with the pulsed air rig. The new composite fan blade design can be evaluated through the process.

Keywords

aeroelasticity pulsed air jet composite plate 

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References

  1. [1]
    Chahine C., Verstraete T., Li H. On the validity of decoupled flutter prediction methods for composite fan blades. International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines, Stockholm, Sweden, 2015.Google Scholar
  2. [2]
    Murugan S., Ganguli R., Harursampath D. Aeroelastic response of composite helicopter rotor with random material properties. Journal of Aircraft, 2008, 45(1): 306–322.CrossRefGoogle Scholar
  3. [3]
    Bordogna M.T., Macquart T., Bettebghor D., Breuker R.D. Aeroelastic optimization of variable stiffness composite wing with blending constraints. AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Washington, USA, 2017.Google Scholar
  4. [4]
    Hong C.H., Chopra I. Aeroelastic stability analysis of a composite rotor blade. Journal of the American Helicopter Society, 1985, 30(2): 57–67.CrossRefGoogle Scholar
  5. [5]
    Weisshaar T.A. Aeroelastic tailoring of forward swept composite wings. Journal of Aircraft, 2012, 18(8): 669–676.CrossRefGoogle Scholar
  6. [6]
    Schuff M., Lengyel-Kampmann T., Forsthofer N. Influence of the steady deformation on numerical flutter prediction for highly loaded and flexible fan blades. ASME Turbo Expo 2017, Charlotte, North Carolina, USA. V07BT36A011.CrossRefGoogle Scholar
  7. [7]
    Ma C., Huang Z., Qi M. Investigation on the forced response of a radial turbine under aerodynamic excitations. Journal of Thermal Science, 2016, 25(2): 130–137.ADSCrossRefGoogle Scholar
  8. [8]
    Song Z., Li F. Active aeroelastic flutter analysis and vibration control of supersonic composite laminated plate. Composite Structures, 2012, 94(2): 702–713.CrossRefGoogle Scholar
  9. [9]
    Stanford B.K., Jutte C.V., Wu K.C. Aeroelastic benefits of tow steering for composite plates. Composite Structures, 2014, 118: 416422.CrossRefGoogle Scholar
  10. [10]
    Scarth C., Sartor P.N., Cooper J.E., Weaver P.M., Silva G.H.C. Robust and reliability-based aeroelastic design of composite plate wings. AIAA Journal, 2016, 55(1): 1–14.Google Scholar
  11. [11]
    Assi G.R.S. Wake-induced vibration of tandem and staggered cylinders with two degrees of freedom, Journal of Fluid and Structures, 2014, 50: 340–357.ADSCrossRefGoogle Scholar
  12. [12]
    Besem F.M., Kamrass J.D., Thomas J.P., Tang D., Kielb R.E. Vortex-induced vibration and frequency lock-in of an airfoil at high angles of attack. Journal of Fluids Engineering, 2016,138(1): 011204.CrossRefGoogle Scholar
  13. [13]
    Chaplin J.R., Batten W. Simultaneous wake-and vortex-induced vibrations of a cylinder with two degrees of freedom in each direction. Journal of Offshore Mechanics & Arctic Engineering, 2014, 136(3): 031101.CrossRefGoogle Scholar
  14. [14]
    Kashimura H., Yasunobu T., Yu S., Setoguchi T. Self-induced oscillation of supersonic jet during impingement on cylindrical body. Journal of Thermal Science, 1998, 7(1): 7–15.ADSCrossRefGoogle Scholar
  15. [15]
    Piraccini M., Di Maio, D., Di Sante, R. Nonlinear modal testing performed by pulsed-air jet excitation system. Nonlinear Dynamics, Volume 1. Conference Proceedings of the Society for Experimental Mechanics Series. Springer, Cham. 2016, pp.155–170.Google Scholar
  16. [16]
    Lin J., Shi Z., Lai H. Numerical study of controlling jet flow and noise using pores on nozzle inner wall. Journal of Thermal Science, 2018,27(2): 146–156.ADSCrossRefGoogle Scholar
  17. [17]
    Xiao J., Chen Y, Zhu Q., Lee J., Ma T. A general ply design for aero engine composite fan blade. ASME Turbo Expo 2017, Charlotte, North Carolina, USA. V07AT30A005.Google Scholar

Copyright information

© Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2018

Authors and Affiliations

  • Hairun Xie
    • 1
  • Yadong Wu
    • 1
  • Anjenq Wang
    • 1
  • Hua Ouyang
    • 1
  1. 1.School of Mechanical EngineeringShanghai Jiao Tong UniversityShanghaiChina

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