叶尖小翼对高亚声速扩压叶栅气动特性影响的数值研究

发布时间：2018-07-09 10:42

  本文选题：高亚声速 + 扩压叶栅　； 参考：《大连海事大学学报》2017年02期

【摘要】：压气机正逐渐向着高负荷、高稳定性的方向发展.为有效控制该趋势下间隙区域内的流动损失加剧现象,可在高亚声速的扩压叶栅中加装叶尖小翼.本文对原型叶片及不同宽度的压力面与吸力面叶尖小翼叶片进行数值研究.结果表明:高亚声速下不同安装方案下的叶尖小翼均可以改善压气机的气动特性,削弱泄漏涡的强度,其中,压力面小翼对于流场的改善效果更为明显,与原型相比,PW2.0的总压损失系数降低了4.47%.
[Abstract]:The compressor is developing towards high load and high stability. In order to effectively control the increase of flow loss in the gap region under this trend, the tip wing can be added to the high subsonic diffuser cascade. In this paper, the tip blade of prototype blade, pressure surface and suction surface with different widths are studied numerically. The results show that the blade tip wing at high subsonic velocity can improve the aerodynamic characteristics of the compressor and weaken the strength of the leakage vortex, and the pressure surface wing can improve the flow field more obviously. Compared with the prototype, the total pressure loss coefficient of PW2.0 is reduced by 4.47.
【作者单位】： 大连海事大学轮机工程学院;
【基金】：国家自然科学基金重点项目(51436002);国家自然科学基金青年科学基金项目(51406021) 中央高校基本科研业务费专项资金资助项目(3132014319;3132016334) 辽宁省高等学校创新团队支持计划资助项目(LT2015004)
【分类号】：TH45
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本文编号：2109099