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涡扇发动机全加力状态收油门过程中分流环参数变化的飞行试验

史建邦 姚尚宏 王玲玲

史建邦, 姚尚宏, 王玲玲. 涡扇发动机全加力状态收油门过程中分流环参数变化的飞行试验[J]. 航空动力学报, 2012, 27(3): 508-512.
引用本文: 史建邦, 姚尚宏, 王玲玲. 涡扇发动机全加力状态收油门过程中分流环参数变化的飞行试验[J]. 航空动力学报, 2012, 27(3): 508-512.
SHI Jian-bang, YAO Shang-hong, WANG Ling-ling. Transient performance of the splitter of turbofan engine from maximum to intermediate thrust in the flight[J]. Journal of Aerospace Power, 2012, 27(3): 508-512.
Citation: SHI Jian-bang, YAO Shang-hong, WANG Ling-ling. Transient performance of the splitter of turbofan engine from maximum to intermediate thrust in the flight[J]. Journal of Aerospace Power, 2012, 27(3): 508-512.

涡扇发动机全加力状态收油门过程中分流环参数变化的飞行试验

Transient performance of the splitter of turbofan engine from maximum to intermediate thrust in the flight

  • 摘要: 通过在飞行条件下对某型涡扇发动机端部厚度分别为1.0mm和1.5mm的分流环静压和变形量进行实时数据采集,得到了不同飞行高度、速度条件下,分流环内外壁面静压值以及分流环的变形量.结果表明:飞机在发动机全加力状态飞行时急收油门过程中,分流环内外壁面静压差值会产生急增,差值增量随飞行速度的增加而增加,分流环厚度越小,增量越大;分流环内外壁面压差是导致分流环变形的主要原因,并给出了该型分流环变形量随压差的变化关系.

     

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出版历程
  • 收稿日期:  2011-05-06
  • 修回日期:  2011-12-23
  • 刊出日期:  2012-03-28

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