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




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This paper presents a comprehensiveinvestigation of aeroelastic stability for a high aft-swept transonic fan bladewith low hub-to-tip ratio. The evolution of the blade’s aeroelastic stabilityin the first bending modes is studied. A 3D flutter computation representingtoday’s industry standard is performed. Steady state flow field andmotion-induced unsteady pressures acting on the blade have been determined by a3D Reynolds-Averaged Navier-Stokes RANS equations with a standard k-εturbulence model. A weakly coupled one-way method has been employed to describethe interaction between fluid and structure. The results of aerodynamic dampingindicate a significant shock-driven risk. To increase the flutter margin by aviable method, a statistical mistuned aeroelastic stability investigation hasbeen performed. It has been found that alternately intentional mistuning with asmall blade frequency offset stabilizes the system effectively. However, as thestandard deviation of random mistuning reaches some critical values, theintroduction of alternately intentional mistuning does not provide any additionalstabilizing effects.

KEYWORDS

Aeroelastic Stability, Flutter, Turbomachinery, Mistuning

Cite this paper

Fu, Z. and Wang, Y. 2015 Aeroelastic Analysis of a Transonic Fan Blade with Low Hub-to-Tip Ratio including Mistuning Effects. Journal of Power and Energy Engineering, 3, 362-372. doi: 10.4236-jpee.2015.34049.





Autor: Zhizhong Fu, Yanrong Wang

Fuente: http://www.scirp.org/



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