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采用平面叶栅模拟压气机动叶叶尖间隙流 被引量:7

EXPERIMENTAL INVESTIGATION OF COMPRESSOR ROTOR TIP LEAKAGE FLOW BY USING A LINEAR CASCADE
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摘要 通过对动叶叶尖进口端壁附面层的性状分析 ,指出采用平面叶栅模拟动叶叶尖间隙流端壁面静止(工况 1 )和仅有端壁面运动 (工况 2 )进口端壁附面层与真实情况的差异。根据转子静止静子转动这一相对运动思想设计出动叶叶尖间隙流实验模型 (工况 3)。对上述 3种工况叶片表面静压分布和叶尖间隙流进行了实验测量。实验表明 :工况 3比 2 ,1叶尖间隙泄漏涡生成得早且间隙泄漏流量较大 ;采用无粘叶尖间隙流计算模型 ,在叶片后面部分计算结果与实测值吻合较好 。 From the analysis of the shape of the end wall boundary layer at the entrance of a rotor blade tip, the discrepancy in the boundary layer, between a linear cascade without end wall motion (denoted here situation No.1) or a linear cascade only with end wall motion (situation No.2) and real circumstances, is pointed out. From the relative motion concept of rotor fixing and stator rotating, the experimental device (situation No.3) for simulating the rotor blade tip clearance flow is designed. In the above three situations, the pressure distribution on the blade surfaces and blade tip leakage flows are measured. The experiments show that the tip leakage vortex in situation No.3 forms earlier and the leakage mass flow rate is larger than in situations No.1 and No.2. The leakage flow calculated using the Rains' model, is satisfactorily agreeable to the experiments over rear part of the blade, but toward the leading edge there is a tendency for the model to overpredict the leakage flow, due to the large streamwise pressure gradient comparable to that across the tip.
出处 《航空学报》 EI CAS CSCD 北大核心 2002年第1期69-71,共3页 Acta Aeronautica et Astronautica Sinica
基金 航空科学基金资助项目 ( 96 C5 2 0 32 )
关键词 压气机转子 叶尖间隙流 平面叶栅 端壁附面层 模拟 compressor compressor rotor tip leakage flow cascade end wall boundary layer
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参考文献6

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