Composing and adding effect of rotor blade unsteady aerodynamic force

DU Hong-jun; LI Gang; HU Jun

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Composing and adding effect of rotor blade unsteady aerodynamic force

更新时间：2026-07-07

- Composing and adding effect of rotor blade unsteady aerodynamic force
- Vol. 24, Issue 9, (2009)
- 作者机构：
  
  1. 空军第一航空学院,信阳,464000
  2. 南京航空航天大学能源与动力学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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DU Hong-jun, LI Gang, HU Jun. Composing and adding effect of rotor blade unsteady aerodynamic force[J]. 2009, 24(9).
DOI：

DU Hong-jun, LI Gang, HU Jun. Composing and adding effect of rotor blade unsteady aerodynamic force[J]. 2009, 24(9). DOI：

摘要

数值模拟了一个带有导叶的单级低速压气机中转子叶片表面的非定常气动力.通过研究转子叶片根部、尖部前缘和尾缘局部位置的非定常气动力

阐明了由尾迹和势扰动两种非定常性诱发的气动力在转子叶片表面的叠加特性.结果表明

上游尾迹的影响波及整个转子叶片弦长范围

而下游静子叶片势扰动仅影响转子叶片尾缘附近的脉动压力

改变上、下游叶片的时序位置

当整个转子叶片表面脉动压力的幅值比最大值减小19.4%时

其叶尖前缘脉动压力的幅值仅比最大值减小9.4%.

Abstract

The rotor blade unsteady aerodynamic force in a single-stage low speed compressor with inlet guide vane(IGV) was simulated numerically in this paper.By analyzing the unsteady blade force located on leading edge and trailing edge of the rotor tip and hub

the adding effect of the upstream wakes and downstream potential effect was illustrated.The upstream wakes affect the whole blade chord range while the downstream potential effect influences only part of the trailing edge.By shifting the clocking position of IGV and stator blade

the amplitude of whole rotor pulsant pressure force can be reduced by 19.4%

while on leading edge of the rotor tip

it can only be reduced by 9.4%.

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