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双层涡轮叶片异形冷却单元内换热特性实验研究 被引量:1

Experimental Study on Heat Transfer Coefficient of Typical Irregular Cooling Configuration in Double-Deck Turbine Guide Vane
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摘要 基于实际加工成型的双层涡轮导向器叶片内部特征,模化出操场形和椭圆形截面冷却结构。针对其内部应用的冲击/气膜复合冷却形式,实验研究了冲击靶面的换热特性,重点分析了通道截面形状不同时,进口Re数、气膜出流以及冲击孔和气膜孔的相对位置对冲击靶面换热特性的影响。研究中发现通道内部局部Nu数呈中心对称的波浪形分布,并且气膜孔壁面上游的换热效果整体低于下游,只有在靠近气膜孔中心局部区域的换热系数较高。随着进气Re数增加,换热效果逐步增强。实验数据表明,截面形状不同的冷却通道的换热特性规律不同。对于操场跑道形冷却通道,冲击孔和气膜孔顺排时冷却效果较好;而椭圆形冷却通道中,冲击孔和气膜孔错排时冷却效果较好。 Cooling structures with playground and oval section are concluded according to the real internal geometry of double-decker turbine guide vane.Experiments are carried out to investigate heat transfer coefficient of hybrid cooling configuration applied in those cooling structures.The influences of coolant Reynolds number,outflow of the film cooling,relative position of impingement holes and film holes on heat transfer characteristics are analyzed in details.There exist periodic peaks and troughs of local heat transfer coefficient due to the impingement.The heat transfer upstream is weakened because of the coolant suction of film outflow,while it can also result in some heat transfer enhancement in the very near region around film hole.It is also found that the performance of hybrid cooling structure increases with the increasing of inlet Reynolds number.Experimental results show that the cooling configuration af-fects heat transfer coefficient greatly and the rules are complicated.For the cooling configuration with playground section,higher cooling performance can be achieved when film holes are arrayed with jet holes sequentially.In the cases of oval section,higher cooling performance is gotten when the impingement holes and the film holes are staggered.
出处 《南京航空航天大学学报》 EI CAS CSCD 北大核心 2016年第3期326-333,共8页 Journal of Nanjing University of Aeronautics & Astronautics
基金 航空推进技术验证计划资助项目
关键词 推进系统 冲击射流 气膜冷却 换热特性 异形单元 propulsion system jet impingement film cooling heat transfer irregular cooling configuration
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