Volume 26 Issue 8
Aug.  2011
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ZHOU Li, ZHANG Xin, CAI Yuan-hu. Unsteady numerical simulation of the turbine blade film cooling[J]. Journal of Aerospace Power, 2011, 26(8): 1695-1701.
Citation: ZHOU Li, ZHANG Xin, CAI Yuan-hu. Unsteady numerical simulation of the turbine blade film cooling[J]. Journal of Aerospace Power, 2011, 26(8): 1695-1701.
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Unsteady numerical simulation of the turbine blade film cooling

  • School of Power and Energy, Northwestern Polytechnical University,Xi'an 710072,China

  • Received Date: 2010-07-23
  • Rev Recd Date: 2010-11-20
  • Publish Date: 2011-08-28
    Abstract
  • The unsteady flowfield of the turbine blade film cooling was investigated numerically,and the influence of unsteady stator/rotor interaction on the blade film cooling effectiveness was discussed.Results show that,the overlying width of the cooling jet flow increases near the downstream of the cooling jet position,when the stator wake is transferred to the cooling jet position,resulting in better film cooling effectiveness at the downstream within 30% arc length range.The fluctuation of the film cooling effectiveness increases with the increment of the blowing rate.Due to the influence of the vortex near the endwall,the cooling jet flow can hardly reach the endwall region,but be entrained to the downstream of the jet position,so the cooling effectiveness is improved correspondingly.

     

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    • References(12)
  • [1]
    Teng S,Han J C,Poinsatte P E.Effect of film-hole shape on turbine-blade heat-transfer coefficient distribution[J].Journal of Thermophysics and Heat Transfer,2001,15(3):249-256.
    [2]
    Schobeiri M T,ztürk B.Experimental study of the effect of periodic unsteady wake flow on boundary layer development,separation,and reattachment along the surface of a low pressure turbine blade.ASME Paper GT2004-53929,2004.
    [3]
    Bons J P,Rivir R B,Mac Arthur C D,et al.The effect of unsteadiness on film cooling effectiveness.AIAA 95-0306,1995.
    [4]
    Garg V K,Abhari R S.Comparison of predicted and experimental Nusselt number for a film-cooled rotating blade.ASME Paper 96-GT-223,1996.
    [5]
    朱惠人,张丽,刘松龄.非定常尾迹对涡轮叶片换热影响的数值模拟[J].推进技术,1999,20(4):53-56. ZHU Huiren,ZHANG Li,LIU Songling.Numercial simulation of influence of unsteady wake on heat transfer of turbine blade[J].Journal of Propulsion Technology,1999,20(4):53-56.(in Chinese)
    [6]
    Kim S T,Hassan I G.Unsteady heat transfer analysis of a film cooling flow.AIAA 2008-1287,2008.
    [7]
    Heidmann J D,Lucci B L,Reshotko E.An experimental study of the effect of wake passing on turbine blade film cooling[J].ASME Journal of Turbomachinery,2001,123(1):214-221.
    [8]
    Narzary D P,Gao Z H,Mhetras S.Effect of unsteady wake on film-cooling effectiveness distribution on a gas turbine blade with compound shaped holes.ASME Paper GT2007-27070,2007.
    [9]
    Gao Z,Narzary D P,Han J C.Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes[J].International Journal of Heat and Mass Transfer,2008,51(10):2139-2152.
    [10]
    Teng S,Sohn D K,Han J C.Unsteady wake effect on film temperature and effectiveness distributions for a gas turbine blade[J].ASME Journal of Turbomachinery,2000,122(2):340-347.
    [11]
    袁锋,竺晓程,杜朝辉.尾迹对气膜冷却影响的三维非定常数值模拟[J].动力工程,2006,26(6):818-821. YUAN Feng,ZHU Xiaocheng,DU Zhaohui.Three dimensional unsteady numerical simulation of the effect of wakes on film cooling[J].Journal of Power Engineering,2006,26(6):818-821.(in Chinese)
    [12]
    Turner M G,Vitt P H,Topp D A,et al.Multistage simulations of the GE90 turbine.NASA-CR-1999-209311,1999.
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