| 双级轴向旋流器性能评估方法（二）——旋流器下游几何结构的影响 |
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| 引用本文： | 张群,闫东博,邢力,徐华胜,邓远灏,钟世林,杨省喆,汪玉明.双级轴向旋流器性能评估方法（二）——旋流器下游几何结构的影响[J].航空动力学报,2017,32(8):1809-1814. |
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| 作者姓名： | 张群 闫东博 邢力 徐华胜 邓远灏 钟世林 杨省喆 汪玉明 |
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| 作者单位： | 1.西北工业大学 动力与能源学院,西安 710072 |
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| 基金项目： | 国家自然科学基金（51676166）； 航天科技创新基金（CASC150708） |
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| 摘 要： | 开展了双级轴向旋流燃烧室反应流场和燃烧性能的理论与数值研究。通过数值模拟研究了旋流强度与旋流器下游（套筒）几何结构对于燃烧室反应流场与燃烧性能的影响规律。结果表明:当旋流强度低时，旋转气流倾向脱离套筒喉部附近的壁面，形成类似喷射的流动；套筒扩张角越大，旋流强度增幅越大；当扩张半角为30°～70°时，气流扩张角随套筒扩张半角增加而增大。研究发现:存在临界套筒扩张半角为73°，大于该临界角时，气流与套筒发生“脱体”现象。通过理论推导与数值仿真相结合的方法，发展建立了套筒出口气流扩张角估算公式。通过与实验及数值结果比较发现，该公式能够对旋流器出口近场气流发展进行准确预测，为未来旋流器的设计提供了一种实用有效的方法。
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| 关 键 词： | 燃烧室 旋流器 旋流强度 套筒 扩张角 |
| 收稿时间： | 2015/11/3 0:00:00 |
Performance evaluation methods of two-stage axial swirlers: Ⅱ influence of swirler rear geometric structure |
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| ZHANG Qun,YAN Dongbo,XING Li,XU Huasheng,DENG Yuanhao,ZHONG Shilin,YANG Xingzhe,WANG Yuming.Performance evaluation methods of two-stage axial swirlers: Ⅱ influence of swirler rear geometric structure[J].Journal of Aerospace Power,2017,32(8):1809-1814. |
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| Authors: | ZHANG Qun YAN Dongbo XING Li XU Huasheng DENG Yuanhao ZHONG Shilin YANG Xingzhe WANG Yuming |
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| Abstract: | Theoretical and numerical studies on the reaction flow field and combustion performance of two-stage axial swirler combustors were carried out. The effects of total swirl number and swirler rear (sleeve) geometric structure size on the reaction flow field and combustion performance were investigated numerically. Results showed that the swirling flow tended to break away from the sleeve throat wall, forming jet-like flow when the total swirl number was small. And the swirling flow intensity increased with the increasing sleeve divergence angle. Airflow divergence angle increased with the increasing sleeve divergence half angle in the range from 30° to 70°. It was found that there was a critical divergence half angle 73° of sleeve. When the angle was greater than the critical angle, the airflow broke away from the sleeve wall. In addition, an empirical formula for estimating the airflow divergence angle of sleeve exit was developed by theoretical method together with numerical simulation. Compared with experimental and numerical results, it is found that the formula can predict the flowfield development downstream the swirlers accurately, providing a practical and effective method for the design of multi-stage swirlers in the future. |
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| Keywords: | combustor swirler swirling intensity sleeve divergence angle |
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