| 涡轮叶栅叶型损失的数值模拟方法 |
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| 引用本文： | 于清,杨弘.涡轮叶栅叶型损失的数值模拟方法[J].航空动力学报,1997,12(2):197-200,222. |
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| 作者姓名： | 于清 杨弘 |
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| 作者单位： | 北京航空航天大学(于清)，哈尔滨工业大学(杨弘) |
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| 摘 要： | 给出了一个计算亚、跨音涡轮叶栅叶型损失的数值计算方法。主流采用时间推进有限体积法求解积分型欧拉方程，并采用了局部网格修正技术；附面层采用全隐格式求解有限差分方程；在叶栅出口与远后方均匀流之间进行了叶片尾迹与主流的掺混损失计算。算例表明本文的数值方法可准确地预测涡轮叶栅的叶型损失。
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| 关 键 词： | 叶型损失 数值模拟 涡轮 叶栅流动 |
| 收稿时间： | 4/1/1996 12:00:00 AM |
| 修稿时间： | 7/1/1996 12:00:00 AM |
A NUMERICAL METHOD FOR PREDICTING TURBINE PROFILE LOSS |
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| Yu Qing and Yang Hong.A NUMERICAL METHOD FOR PREDICTING TURBINE PROFILE LOSS[J].Journal of Aerospace Power,1997,12(2):197-200,222. |
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| Authors: | Yu Qing and Yang Hong |
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| Institution: | 4th Dept.Beijing University of Aeronautics and Astronautics, Beijing 100083;2th Dept. Harbin Institute of Technology, Harbin 150001 |
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| Abstract: | A new numerical method for predicting the profile loss of turbine blades in subsonic and supersonic flows is presented.The profile loss consists of two parts:friction loss in the boundary layer on pressure and suction surfaces and mixing loss due to the interaction between wake and mainstream.A time-marching finite-volume Euler solver is used for mainstream calculation while a finite-difference computation for the boundary layer.A local C-grad correction is used in mainstream calculation and a full implicit difference scheme is applied to the boundary layer calculation.On the basis of mass,momentum and energy consrvation laws,the mixing loss is obtained between cascade exit and the far uniform downstream and compared with several experimental data.It is shown that this numerical method can make quite precise prediction of turbine blade profile loss. |
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| Keywords: | Profile losses Numerical simulation Turbines cascade flow |
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