Tip leakage flow and heat transfer characteristics with effect of trailing edge cutback on squealer tip
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摘要: 通过数值计算对带有尾缘开槽结构的突肩叶尖间隙流场结构、泄漏流量、泄漏损失、表面传热系数进行了对比研究.研究结果显示:相比全突肩叶尖,吸力侧尾缘开槽突肩叶尖可以改变开槽附近泄漏流的流动路径,有效抑制其与主流的掺混.压力侧尾缘开槽和吸力侧尾缘开槽均会增加间隙泄漏流量.压力侧尾缘开槽突肩叶尖会增加间隙泄漏损失,开槽长度越大损失越大.研究范围内的吸力侧尾缘开槽均会减小间隙泄漏损失,但存在最佳开槽长度.压力侧和吸力侧尾缘开槽均会轻微地增加叶尖表面传热系数.Abstract: Comparative study was carried out to investigate the leakage flow field, leakage mass flow rate, leakage flow loss and surface heat transfer coefficient of trailing edge cutback on squealer tips by numerical simulations. Research results show that the suction side trailing edge cutback on squealer tips can change the leakage flow path near the cutback area, and suppress the mixing of the leakage flow and the main stream effectively compared with the cavity tip. Both suction and pressure sides trailing edge cutback on squealer tips can increase the leakage mass flow rate. Pressure side trailing edge cutback on squealer tips can increase the tip clearance leakage flow loss with the increase of cutback length. Suction side trailing edge cutback on squealer tips within the studied range can decrease the tip leakage flow loss, but there is an optimum cutback length. Both pressure and suction sides trailing edge cutback on squealer tips can increase the tip surface heat transfer coefficient slightly.
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Key words:
- turbine /
- tip clearance /
- leakage mass flow rate /
- leakage flow loss /
- surface heat transfer coefficient
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[1] Denton J D.Loss mechanisms in turbomachines[R].ASME Paper 93-GT-435,1993. [2] Azad G M S,Han J C,Bunker R S,et al.Effect of squealer geometry arrangement on a gas turbine blade tip heat transfer[J].Journal of Heat Transfer,2002,124(3):452-459. [3] Azad G M S,Han J C,Boyle R J.Heat transfer and flow on the squealer tip of a gas turbine blade[J].Journal of Turbomachinery,2000,122(4):725-732. [4] Kwak J S,Han J C.Heat transfer coefficients on the squealer tip and near-tip regions of a gas turbine blade with single or double squealer[J].Journal of Heat Transfer,2003,125(4):778-787. [5] Kwak J S,Han J C.Effects of rim location,rim height,and tip clearance on the tip and near tip region heat transfer of a gas turbine blade[J].International Journal of Heat and Mass Transfer,2004,47(2):5651-5663. [6] Krishnababu S K,Newton P J,Lock G D,et al.Aero-thermal investigation of tip leakage flow in axial flow turbines:Part I effect of tip geometry and tip clearance gap[R].ASME Paper GT2007-27954,2007. [7] El-Gabry L A.Numerical modeling of heat transfer and pressure losses for an uncooled gas turbine blade tip effect of tip clearance and tip geometry[R].ASME Paper GT2007-27008,2007. [8] Prakash C,Lee C P,Cherry D G,et al.Analysis of some improved blade tip concepts[J].Journal of Turbomachinery,2006,128(7):639-642. [9] Lee S W,Kim S U.Tip gap height effects on the aerodynamic performance of a cavity squealer tip in a turbine cascade in comparison with plane tip results:Part 1 tip gap flow structure[J].Experiments in Fluids,2010,49(4):1039-1051. [10] 高杰,郑群.叶顶凹槽形态对动叶气动性能的影响[J].航空学报,2013,34(2):218-226. GAO Jie,ZHENG Qun.Effect of squealer tip geometry on rotor blade aerodynamic performance[J].Acta Aeronautica et Astronautica Sinica,2013,34(2):218-226.(in Chinese) [11] Nasir H,Ekkad S V,Kontrovitz D M,et al.Effect of tip gap and squealer geometry on detailed heat transfer measurements over a high pressure turbine rotor blade tip[J].Journal of Turbomachinery,2004,126(2):221-228. [12] Camci C,Dey D,Kavurmacioglu L.Aerodynamics of tip leakage flow near partial squealer rims in an axial flow turbine stage[J].Journal of Turbomachinery,2005,127(3):14-24. [13] Mhetras S,Narzary D,Gao Z H,et al.Effect of cutback squealer and cavity depth on film-cooling effectiveness on a gas turbine blade tip[J].Journal of Turbomachinery,2008,130(2):111-120. [14] Acharya S, Kramer G,Moreaux L,et al.Squealer tip heat transfer with film cooling[R].ASME Paper GT2010-23688, 2010. [15] Naik S,Georgakis C,Hofer T,et al.Heat transfer and film cooling of blade tips and endwalls[R].ASME Paper GT2010-23288,2010. [16] Bindon J P,Morphus G.The effect of relative motion,blade edge radius and gap size on the blade tip pressure distribution in an annular turbine cascade with clearance[R].ASME Paper 88-GT-256,1988. [17] Bindon J P.The measurement and formation of tip clearance loss[J].Journal of Turbomachinery,1989,111(3):258-263. [18] Timko L P.Energy efficient engine high pressure turbine component test performance report[R].NASA CR-168289,1984.
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