Effect of inlet wake angle on compressor stator loading

YANG Rong-fei; LI Qiu-shi; LI Zhi-ping; ZHOU Sheng

Chinese

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Effect of inlet wake angle on compressor stator loading

更新时间：2026-07-07

- Effect of inlet wake angle on compressor stator loading
- Vol. 25, Issue 12, (2010)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院航空发动机气动热力科技重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2010
- 稿件说明：
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YANG Rong-fei, LI Qiu-shi, LI Zhi-ping, et al. Effect of inlet wake angle on compressor stator loading[J]. 2010, 25(12).
DOI：

YANG Rong-fei, LI Qiu-shi, LI Zhi-ping, et al. Effect of inlet wake angle on compressor stator loading[J]. 2010, 25(12). DOI：

摘要

压气机叶片负荷的提高使得叶片表面边界层更容易分离

利用上游叶排产生的非定常尾迹能够抑制边界层分离.运动圆柱代替上游转子

在保证下游叶片进气速度大小及攻角不变的情况下

改变圆柱运动速度以获得上游尾迹与下游静叶吸力面不同的夹角

发现在低负荷小分离情况下静叶损失系数与上游尾迹入射角无关;高负荷大分离情况下静叶损失系数随上游尾迹入射角的增加而降低.分析尾迹作用下高负荷静叶通道内流场

当进入静叶通道的尾迹与叶片吸力面近似平行时

尾迹诱导边界层增厚.使得叶片表面分离泡随时间大幅值脉动

损失增加;当尾迹与叶片吸力面的角度逐渐垂直时

尾迹抑制了边界层分离

同时叶片表面分离泡位置近似不变

其原因是尾迹以负射流形式进入边界层内部

补充了边界层内部低能流体

使得损失减小.

Abstract

With increase of the compressor loading

the blade surface boundary layer was easily separated but suppressed by unsteady upstream wake.In this paper

moving cylinder was used to produce unsteady wake

and different inlet wake angles were acquired by changing moving speed.This shows that the performance of stator will be improved on high blade loading while it varies little on low blade loading as the inlet wake angle increases.During the interaction of wake and boundary on high blade loading

increasing inlet wake angle will enhance the energy exchange between wake and boundary layer

which is a main factor to suppress the separated boundary layer and reduce the stator loss.

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