| 一种微型涡轮发动机导向器改进方案 |
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| 引用本文： | 宣建光,邱建,夏晨,黄国平.一种微型涡轮发动机导向器改进方案[J].航空动力学报,2010,25(12):2690-2696. |
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| 作者姓名： | 宣建光 邱建 夏晨 黄国平 |
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| 作者单位： | 南京航空航天大学能源与动力学院,南京,210016 |
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| 摘 要： | 为了提高发动机性能,克服微型涡轮发动机(MTE)的尺度小等因素导致其导向器内流动损失大的缺点,采用了整体叶片式导向器设计技术对某MTE-C微型发动机涡轮导向器进行了改型设计.首先采用NAPA软件对MTE-C微型发动机的整体叶片式导向器进行数值模拟,通过流场分析得到了原型导向器设计中导致流动效率低下的不足之处,并以此为理论依据,对导向器进行了改进.改进型导向器的整级数值模拟结果表明,涡轮在设计点的效率提高了15%,且在宽广的工作范围内其通流能力和效率均得到了明显的提升.
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| 关 键 词： | 涡轮发动机 微型 导向器 数值模拟 改进 |
| 收稿时间： | 2009/11/15 0:00:00 |
| 修稿时间： | 4/12/2010 4:30:56 PM |
Improvement of a micro-turbine nozzle |
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| XUAN Jian-guang,QIU Jian,XIA Chen and HUANG Guo-ping.Improvement of a micro-turbine nozzle[J].Journal of Aerospace Power,2010,25(12):2690-2696. |
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| Authors: | XUAN Jian-guang QIU Jian XIA Chen and HUANG Guo-ping |
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| Institution: | Institute of Micro Engineering, Nanjing University of Aeronautics and Astronautics,Iinstitute of Micro Engineering, Nanjing University of Aeronautics and Astronautics,Institute of Micro Engineering, Nanjing University of Aeronautics and Astronautics,Institute of Micro Engineering, Nanjing University of Aeronautics and Astronautics |
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| Abstract: | The compact configuration and small size of the micro-turbine engine cause the large flow loss in the micro turbine nozzle, so the turbine nozzle is modified to reduce the flow loss and improve the performance. The numerical simulation of the original turbine nozzle was completed by NAPA program, and the reasons which caused the low performance were got by flow field analysis. The vaned turbine nozzle is improved and the performance comparison between original and improvement turbine nozzle was completed. The efficiency of turbine stage at designing point increases 15%, and the flow rate and efficiency of turbine stage are enhanced remarkably within a wide working range. |
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| Keywords: | turbine engine micro turbine nozzle numerical simulation improvement |
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