| 反旋喷嘴进气旋转盘腔压力损失特性 |
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| 引用本文： | 呼艳丽,郭文,王蕾,罗翔. 反旋喷嘴进气旋转盘腔压力损失特性[J]. 航空动力学报, 2016, 31(8): 1866-1873. DOI: 10.13224/j.cnki.jasp.2016.08.010 |
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| 作者姓名： | 呼艳丽 郭文 王蕾 罗翔 |
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| 作者单位： | 1. 中国航空工业集团公司中国燃气涡轮研究院, 成都 610500; |
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| 摘 要： | 针对旋转盘腔的压力损失问题，利用反旋喷嘴改变进入旋转盘腔的气流的切向速度，减少旋转腔内涡的生成，从而减小气体流经旋转盘腔的压力损失.通过实验的方法测得反旋进气条件下的流阻特性，应用k-ω SST模型模拟了不同工况下腔内的流场.研究表明:旋转盘腔内的压降由湍流参数和掺混后旋流系数共同控制.喷嘴自身压降所占比例为极大值时，腔内无大涡出现，而在非极值点的工况下，腔内均为对涡的流动结构.
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| 关 键 词： | 旋转盘腔 径向内流 反旋喷嘴 压力损失 旋流系数 流动结构 |
| 收稿时间： | 2014-12-08 |
Pressure loss characteristics in a rotating cavity with de-swirled nozzles |
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| HU Yan-li,GUO Wen,WANG Lei and LUO Xiang. Pressure loss characteristics in a rotating cavity with de-swirled nozzles[J]. Journal of Aerospace Power, 2016, 31(8): 1866-1873. DOI: 10.13224/j.cnki.jasp.2016.08.010 |
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| Authors: | HU Yan-li GUO Wen WANG Lei LUO Xiang |
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| Affiliation: | 1. China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China;2. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | De-swirled nozzles were fitted in a rotating cavity to reduce the inlet flow tangential velocity thus to reduce the pressure loss associated with radial inflow in the cavity. In this work, experiments were conducted to measure the pressure difference through the test rig and k-ω SST model was applied to simulate the flow structures. Experimental results revealed that the proportion of pressure loss through nozzles to the overall pressure loss through test rig exists maximum and non-maximum conditions. While the proportion of pressure loss through nozzles to the overall pressure loss reaches the top there are no large scale vortex. In the other conditions there are always two large scale vortexes in the cavity, which lead to the largest pressure loss in the rotating cavity. |
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| Keywords: | rotating cavity radial inflow de-swirl nozzles pressure loss swirl ratio flow structure |
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