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轴向非均匀凹槽叶顶的实验与数值研究

孟庆鹤 陈绍文 刘宏言 王松涛

孟庆鹤, 陈绍文, 刘宏言, 王松涛. 轴向非均匀凹槽叶顶的实验与数值研究[J]. 航空动力学报, 2019, 34(8): 1813-1821. doi: 10.13224/j.cnki.jasp.2019.08.022
引用本文: 孟庆鹤, 陈绍文, 刘宏言, 王松涛. 轴向非均匀凹槽叶顶的实验与数值研究[J]. 航空动力学报, 2019, 34(8): 1813-1821. doi: 10.13224/j.cnki.jasp.2019.08.022
Experimental and numerical study on axially non-uniform clearances with a squealer cavity tip[J]. Journal of Aerospace Power, 2019, 34(8): 1813-1821. doi: 10.13224/j.cnki.jasp.2019.08.022
Citation: Experimental and numerical study on axially non-uniform clearances with a squealer cavity tip[J]. Journal of Aerospace Power, 2019, 34(8): 1813-1821. doi: 10.13224/j.cnki.jasp.2019.08.022

轴向非均匀凹槽叶顶的实验与数值研究

doi: 10.13224/j.cnki.jasp.2019.08.022
基金项目: 国家自然科学基金(51776048,5136002)

Experimental and numerical study on axially non-uniform clearances with a squealer cavity tip

  • 摘要: 为探究不同轴向非均匀凹槽间隙控制泄漏流动的效果和机理,采用实验与数值结合的研究方法,对两种间隙条件下的叶顶凹槽结合渐缩型间隙、均匀型间隙和渐扩型间隙方案对涡轮叶顶泄漏流动的控制效果进行研究。结果表明:减小泄漏流流量与控制叶栅总压损失之间没有直接联系,渐扩型间隙增大了26.7%的泄漏流流量,但在小间隙和大间隙条件下分别减小了2.44%和3.53%的总压损失;渐扩间隙减小总压损失,是通过有效减小通道涡在节距向和展向的尺度,并在一定程度上减小泄漏涡在节距向的尺度实现的;渐扩间隙减小通道涡和泄漏涡的尺度,其原理在于渐扩间隙的布置增强了凹槽内的径向流动,使压力面再附线更靠近叶片,吸力面泄漏涡分离线位置更靠后,从而抑制了泄漏流动。

     

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出版历程
  • 收稿日期:  2019-03-18
  • 刊出日期:  2019-08-28

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