| 内部冲击和外部气膜的组合特性研究 |
| |
| 引用本文： | 丁水汀,崔亮,孙纪宁,陶智,徐国强,李秋实.内部冲击和外部气膜的组合特性研究[J].航空动力学报,2007,22(2):187-192. |
| |
| 作者姓名： | 丁水汀 崔亮 孙纪宁 陶智 徐国强 李秋实 |
| |
| 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重点实验室,北京,100083 |
| |
| 基金项目： | 教育部跨世纪优秀人才培养计划 |
| |
| 摘 要： | 利用数值模拟的方法研究了一种外部稀疏气膜和内部冲击复合的导向器叶片冷却结构.研究的重点是气膜孔和冲击孔的相对位置以及气膜孔直径对叶盆和叶背冷却效率的影响规律,并对叶盆区域和叶背区域的综合冷却效率和热均匀性做了讨论.计算表明:在计算所选取的参数范围内,气膜孔直径的增大提高了叶盆区域的综合冷却效率,而对叶背区域的影响规律则较为复杂;综合考虑叶盆叶背的冷却效率和热均匀性,气膜孔的位置在单元腔的前部时冷却效果最好.
|
| 关 键 词： | 航空、航天推进系统 气膜冷却 冲击冷却 冷却效率 数值模拟 |
| 文章编号： | 1000-8055(2007)02-0187-06 |
| 收稿时间： | 2006/1/17 0:00:00 |
| 修稿时间： | 2006年1月17日 |
Combined features of the inner impingement and outer film cooling holes of a vane |
| |
| DING Shui-ting,CUI Liang,SUN Ji-ning,TAO Zhi,XU Guo-qiang and LI Qiu-shi.Combined features of the inner impingement and outer film cooling holes of a vane[J].Journal of Aerospace Power,2007,22(2):187-192. |
| |
| Authors: | DING Shui-ting CUI Liang SUN Ji-ning TAO Zhi XU Guo-qiang and LI Qiu-shi |
| |
| Institution: | National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
| |
| Abstract: | Numerical simulation has been used to investigate a cooling configuration of a guide turbine vane.This vane has outer sparse film cooling holes and inner impingement holes.In this paper,we mainly studied how different positions and diameters of the film cooling holes influenced the cooling efficiency on the pressure and suction sides of the vane;and discussed the cooling efficiency and uniformity of temperature distribution on the pressure and suction sides of the vane.The computational results show that,within the parameters used in this simulation,the increase in the film cooling hole diameters obviously improves the cooling efficiency on the pressure side of the vane,but the effect is more complicated on the suction side.Considering the cooling efficiency and the uniformity of temperature distribution on the pressure and suction sides of the vane,the position of the film cooling holes located on the front side of the chamber results in the best cooling efficiency. |
| |
| Keywords: | aerospace propulsion system film cooling impingement cooling cooling efficiency numerical simulation |
| 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 |
|
