| 涡轮风扇发动机紧凑压缩系统气动性能 |
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| 引用本文： | 阙晓斌,侯安平,周盛.涡轮风扇发动机紧凑压缩系统气动性能[J].航空动力学报,2011,26(2):297-303. |
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| 作者姓名： | 阙晓斌 侯安平 周盛 |
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| 作者单位： | 北京航空航天大学,能源与动力工程学院航空发动机气动热力国家级重点实验室,北京,100191 |
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| 摘 要： | 通过数值方法研究了由2级风扇、4级高压压气机及外涵组成的紧凑压缩系统的气动性能.探讨了双涵双轴压缩系统气动性能的评估方法及数值计算中相应的边界给定方法.通过对紧凑压缩系统的一体化数值模拟,分别获取了风扇及高压压气机的设计转速特性,并与设计值进行了对比,结果表明流量、压比、效率都达到了设计要求,而风扇失速裕度仅为7.8%...
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| 关 键 词： | 涡轮风扇发动机 风扇/压气机 紧凑压缩系统 双涵 分流环 |
| 收稿时间： | 1/6/2010 12:00:00 AM |
| 修稿时间： | 2010/6/30 0:00:00 |
Aerodynamic performance investigation of a compact compression system for turbofan engine |
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| QUE Xiao-bin,HOU An-ping and ZHOU Sheng.Aerodynamic performance investigation of a compact compression system for turbofan engine[J].Journal of Aerospace Power,2011,26(2):297-303. |
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| Authors: | QUE Xiao-bin HOU An-ping and ZHOU Sheng |
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| Institution: | National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China |
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| Abstract: | The performance of a compact compression system with fan-bypass-core compressor configuration was investigated numerically in this paper.The throttling methodology for accessing performance of fan-bypass-core compression system and its implementation during the numerical simulation was discussed.The calculated design speed performance of fan and high pressure compressor (HPC) shows that the design targets are achieved for mass flow,total pressure ratio and efficiency,while the stall margin of fan is only 7.8%,lower than the required value.Analysis of the flow field evolution shows that,during core nozzle throttling,the system instability is initiated in the exit stage of HPC;during bypass nozzle throttling,however,the large extent blockage,which is caused by the interaction of rotor tip vortex and passage shock,may contribute to the instability of the compression system. |
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| Keywords: | turbofan engine fan/compressor compact compression system fan bypass splitter |
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