| 大扩张角子午流道型线对损失的影响 |
| |
| 引用本文： | 安柏涛,韩万金,王松涛,王仲奇.大扩张角子午流道型线对损失的影响[J].推进技术,2001,22(3):211-214. |
| |
| 作者姓名： | 安柏涛 韩万金 王松涛 王仲奇 |
| |
| 作者单位： | 哈尔滨工业大学能源科学与工程学院, |
| |
| 基金项目： | 国家自然科学基金(59636180)和教育部博士点基金EDAF 24403003。 |
| |
| 摘 要： | 采用数值计算方法对具有大扩张中间机匣的某型涡轮低压级子午流道型线进行了改型设计，提出了7种型线设计方案，并应用N－S方程全三维粘性求解程序对7种方案进行了验算，结果表明：子牛扩张型流道外壁型线的改变，对低压导向器出口能量损失的影响是显著的，设计气动性能优良的子午扩张型线能明显削弱由于大扩张角引起的气流分离，降低涡轮低压级的损失。
|
| 关 键 词： | 航空发动机 涡轮叶栅 叶栅流 数值计算 壁面线 改型设计 大扩张角 损失影响 |
| 文章编号： | 1001-4055（2001）03-0211-04 |
| 修稿时间： | 2000年9月4日 |
Effects of diffused meridional passage contour on loss |
| |
| AN Bai-tao,HAN Wan-jin,WANG Song-tao and WANG Zhong-qi.Effects of diffused meridional passage contour on loss[J].Journal of Propulsion Technology,2001,22(3):211-214. |
| |
| Authors: | AN Bai-tao HAN Wan-jin WANG Song-tao and WANG Zhong-qi |
| |
| Institution: | School of Energy Science and Engineering, Harbin Inst. of Technology, Harbin 150001,China;School of Energy Science and Engineering, Harbin Inst. of Technology, Harbin 150001,China;School of Energy Science and Engineering, Harbin Inst. of Technology, Harbin 150001,China;School of Energy Science and Engineering, Harbin Inst. of Technology, Harbin 150001,China |
| |
| Abstract: | The numerical calculation was carried out to contour design of low pressure turbine which has great diffused angle casing. Seven schemes were bought forward and testified by 3D N-S solver. The results show that the change of shroud of diffused meridional passage have great effect on energy loss at exit of low pressure guide vane. The excellent aerodynamic performance design of shroud of diffused meridional passage can weaken flow separation which caused by great diffused angle and reduce the loss. |
| |
| Keywords: | Aircraft engine Turbine cascade Cascade flow Numerical calculation Wall line Contour design |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
| 点击此处可从《推进技术》浏览原始摘要信息 |
| 点击此处可从《推进技术》下载免费的PDF全文 |
