Volume 31 Issue 1
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ZHAO Guo-qing, ZHAO Qi-jun, WU Qi, WANG Bo. Analyses on inhibiting of transonic characteristics of rotor with new type blade-tip[J]. Journal of Aerospace Power, 2016, 31(1): 143-152. doi: 10.13224/j.cnki.jasp.2016.01.019
Citation: ZHAO Guo-qing, ZHAO Qi-jun, WU Qi, WANG Bo. Analyses on inhibiting of transonic characteristics of rotor with new type blade-tip[J]. Journal of Aerospace Power, 2016, 31(1): 143-152. doi: 10.13224/j.cnki.jasp.2016.01.019
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Analyses on inhibiting of transonic characteristics of rotor with new type blade-tip

doi: 10.13224/j.cnki.jasp.2016.01.019

  • National Key Laboratory of Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • Received Date: 2014-05-22
  • Publish Date: 2016-01-28
    Abstract
  • To investigate effects of different new type blade tips on transonic characteristics of helicopter rotor, numerical analyses about the impacts of blade tips on the local flow details and aerodynamic characteristics near blade-tip were carried out. A high-precision CFD method was developed with a highly-efficient embedded grid method for the simulation of the rotor flowfield. Based on these methods, the influences of shape of blade tip on the intensity of shock wave, shock-boundary layer interference, blade tip wake and aerodynamic performance of rotor were analyzed at a transonic state respectively. The numerical results indicate that backward sweep and dihedral shape of blade tip have a smaller effect on reducing the transonic characteristics of rotor, but forward sweep and anhedral shape of blade tip can effectively reduce the transonic region, the intensity of shock wave and flow separation induced by the shock-boundary layer interference. Furthermore, sweepback blade-tip has a remarkable effect in reducing rotor torque, and straight forward sweep blade-tip can effectively reduce rotor torque (12.3% reduction of rotor torque for the case of straight forward sweep 30°) at larger rotor disc loading state, and anhedral blade-tip can effectively inhibit the blade tip vortex intensity (50% reduction of vorticity magnitude of blade-tip vortex for the case of anhedral 30°) and accelerate the dissipation of blade-tip vortex wake.

     

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