| 民用航空涡轮发动机短舱高速风洞试验 |
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| 引用本文： | 陈俊,章欣涛,冯丽娟.民用航空涡轮发动机短舱高速风洞试验[J].航空动力学报,2019,34(7):1416-1424. |
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| 作者姓名： | 陈俊 章欣涛 冯丽娟 |
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| 作者单位： | 中国航空发动机集团有限公司商用航空发动机有限责任公司,上海,201108;中国航空发动机集团有限公司商用航空发动机有限责任公司,上海,201108;中国航空发动机集团有限公司商用航空发动机有限责任公司,上海,201108 |
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| 摘 要： | 为了获取三种不同型面的民用航空涡轮发动机短舱气动特性,开展了高速风洞试验与数值仿真研究,获取了短舱的压力分布及内流特性,并对比分析了风洞试验数据与仿真结果。结果表明:随着流量系数减小及攻角增加,短舱上唇口外流出现分离;随着流量系数增大,短舱内流下侧出现分离;采用的CFD方法在无分离情况下静压分布与试验结果吻合,但随着流量系数的减小,CFD结果先于试验出现了气流分离。
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| 关 键 词： | 航空涡轮发动机 短舱 进气道 静压分布 风洞试验 |
| 收稿时间： | 2018/10/17 0:00:00 |
High speed wind tunnel test of civil aviation turbine engine nacelle |
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| Abstract: | Research of three different civil aviation turbine engine nacelle profiles by high speed wind tunnel test and numerical simulation method was finished, and the static pressure distribution and induct performance of nacelle were obtained. By comparing the result of wind tunnel test with the numerical simulation, it showed that nacelle upside cowl would have separation when the mass flow rates reduced or the attack angle increased; the induct of downside would have separation when the mass flow rates increased; the numerical simulation result of static pressure distribution coincided with the wind tunnel result when there was no separation, but when mass flow rate reduced, the CFD results were separated before the test. |
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| Keywords: | aviation turbine engine nacelle inlet static pressure distribution wind tunnel test |
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