| 涡轮叶片型面气膜孔流量系数的计算方法 |
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| 引用本文： | 向安定,刘松龄,朱惠人.涡轮叶片型面气膜孔流量系数的计算方法[J].推进技术,2005,26(1):24-27. |
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| 作者姓名： | 向安定 刘松龄 朱惠人 |
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| 作者单位： | 1. 北京动力机械研究所,北京,100074
2. 西北工业大学,动力与能源学院,陕西,西安,710072 |
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| 基金项目： | 航空科学基金资助项目 (00C53028)。 |
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| 摘 要： | 在Rowbury D A等提出的算法基础上进行了改进，使该算法更适合用来计算压比较小情况下尤其是叶片前缘区域的气膜孔流量系数。该算法主要考虑了气膜孔出口主流流动状况、气膜孔几何参数和孔内流动雷诺数对气膜孔流量系数的影响。经过实验数据对比验证，表明该算法可能成为设计型面气膜冷却的一种通用方法。
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| 关 键 词： | 涡轮叶片 薄膜冷却 流量系数 计算 实验 |
| 文章编号： | 1001-4055(2005)01-0024-04 |
| 修稿时间： | 2003年12月1日 |
A method for discharge coefficients computation of film cooling holes on blade surface of turbine cascade |
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| XIANG An-ding,LIU Song-ling and ZHU Hui-ren.A method for discharge coefficients computation of film cooling holes on blade surface of turbine cascade[J].Journal of Propulsion Technology,2005,26(1):24-27. |
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| Authors: | XIANG An-ding LIU Song-ling and ZHU Hui-ren |
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| Institution: | XIANG An-ding~1,LIU Song-ling~2,ZHU Hui-ren~2 |
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| Abstract: | The empirical means for prediction of discharge coefficients of film cooling holes on the turbine blade suggested by Rowbury D A et al was improved to adapt the computations in the cases of low pressure ratios and the holes in leading edge region especially. The effects of external cross flow, hole geometry and Reynold number in the hole were taken into account. An additive loss coefficient method is subsequently applied to the test data in order to show the effect of the external crossflow. To compare with great deal of experimental data, the result shows the improved method may be used as a generalized design methodology of film cooling for turbine blade. |
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| Keywords: | Turbine blade Film cooling Flow coefficient Computation Experimentation |
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