涡轮风扇发动机紧凑压缩系统气动性能

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

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

基金项目: 国家自然科学基金(60934001)

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出版历程
- 收稿日期: 2010-01-06
- 修回日期: 2010-06-30
- 刊出日期: 2011-02-28

Aerodynamic performance investigation of a compact compression system for turbofan engine

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

摘要

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%,低于设计指标.对节流过程中流动分析表明,内涵节流时,压缩系统的失稳起始于高压压气机出口级;外涵节流时,风扇进口级叶尖泄露涡在通道激波作用下发生破裂,导致较大范围的堵塞,是压缩系统失稳的主要原因.
- 涡轮风扇发动机 /
- 风扇/压气机 /
- 紧凑压缩系统 /
- 双涵 /
- 分流环
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.
- turbofan engine /
- fan/compressor /
- compact compression system /
- fan bypass /
- splitter

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参考文献(16)

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