| 上游尾迹入射角对压气机叶片负荷的影响 |
| |
| 引用本文： | 杨荣菲,李秋实,李志平,周盛.上游尾迹入射角对压气机叶片负荷的影响[J].航空动力学报,2010,25(12):2711-2715. |
| |
| 作者姓名： | 杨荣菲 李秋实 李志平 周盛 |
| |
| 作者单位： | 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 |
| |
| 基金项目： | 国家自然科学基金(10902008); “凡舟”青年科研基金(20090401) |
| |
| 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.
|
| 关 键 词： | 压气机 尾迹 非定常流动 边界层分离 高叶片负荷 |
| 收稿时间： | 2009/12/3 0:00:00 |
| 修稿时间： | 4/9/2010 12:00:00 AM |
Effect of inlet wake angle on compressor stator loading |
| |
| YANG Rong-fei,LI Qiu-shi,LI Zhi-ping and ZHOU Sheng.Effect of inlet wake angle on compressor stator loading[J].Journal of Aerospace Power,2010,25(12):2711-2715. |
| |
| Authors: | YANG Rong-fei LI Qiu-shi LI Zhi-ping and ZHOU Sheng |
| |
| Institution: | National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100091,China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100091,China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100091,China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100091,China |
| |
| 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. |
| |
| Keywords: | compressor wake unsteady flow separated boundary layer |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
