Aerodynamic performance investigation of a compact compression system for turbofan engine

QUE Xiao-bin; HOU An-ping; ZHOU Sheng

Chinese

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Aerodynamic performance investigation of a compact compression system for turbofan engine

更新时间：2026-07-07

- Aerodynamic performance investigation of a compact compression system for turbofan engine
- Vol. 26, Issue 2, (2011)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
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QUE Xiao-bin, HOU An-ping, ZHOU Sheng. Aerodynamic performance investigation of a compact compression system for turbofan engine[J]. 2011, 26(2).
DOI：

QUE Xiao-bin, HOU An-ping, ZHOU Sheng. Aerodynamic performance investigation of a compact compression system for turbofan engine[J]. 2011, 26(2). DOI：

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.

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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Shenyang Aeroengine Design and Research Institute, Aviation Industry Corporation of China

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