|
| 翼型近壁区固液两相流场特性研究 |
| Study on the characteristics of solid-liquid two-phase flow field in the near wall of airfoil |
| 投稿时间：2024-09-29 修订日期：2025-02-21 |
| DOI： |
| 中文关键词: 流场测试 数值模拟 固液两相流 近壁区 速度滑移 |
| 英文关键词:flow field test numerical simulation near wall zone solid-liquid flow velocity-slip |
| 基金项目: |
|
| 摘要点击次数: 108 |
| 全文下载次数: 0 |
| 中文摘要: |
| 为研究翼型近壁区固液两相速度滑移规律，本文采用欧拉-欧拉两相流模型和RNG k-ε湍流模型对来流冲角为10°的翼型进行了固液两相流数值模拟，并结合PIV流场测试结果，系统研究了翼型近壁区固液两相的速度滑移规律。结果表明：翼型近壁区存在固液两相速度滑移，距离壁面越近速度滑移程度越高；翼型前缘固液两相最大速度差为0.83m/s、最大角度差为11.3°，主要发生在冲击点附近的速度剧变区；翼型体沿翼弦方向由于速度均匀减小，速度滑移程度也较小，翼型尾部速度滑移程度相对较高，翼型体两相间最大速度差为0.39m/s、最大角度差为0.6°。翼型前缘近壁区速度滑移程度高于翼型体近壁区。 |
| 英文摘要: |
| In this study, the Euler-Euler two-phase flow model and the RNG k-ε turbulence model are used to simulate the solid-liquid two-phase flow in the airfoil with an angle of impact of 10°. In combination with the PIV flow field test, the velocity-slip law of the solid-liquid phase near the wall of the airfoil is investigated. The conclusions from the study are: Velocity-slip exists in the near-wall of the airfoil, and the closer distance to the wall, the higher velocity slip degree; The maximum velocity-slip between the two phases at the leading edge of the airfoil is 0.83m/s and the maximum angle difference is 11.3°, which mainly occurs in the velocity upheaval area near the impact point; Because of the velocity of airfoil decreases uniformly along the airfoil chord, the velocity-slip degree is relatively smaller, the degree of airfoil tail is relatively high. The maximum velocity difference between the two phases of the airfoil body is 0.39m/s, and the maximum angle difference is 0.6°. The velocity-slip in the near wall of the airfoil leading edge is higher than that in the near wall of the airfoil body. |
| 查看/发表评论 下载PDF阅读器 |
| 关闭 |
