航天器环境工程2025，Vol.42Issue(2)：136-143,8.DOI:10.12126/see.2024129
航空发动机试验舱进气整流系统设计及数值验证
Design and numerical validation on the intake smoothing system for aeroengine test chamber
白冰 1富钰 1邵钰杰 1韩潇 1龚洁 1吕世增 1赵月帅 1杨波 1李国华 1张立明1
作者信息
- 1. 北京卫星环境工程研究所,北京 100094
- 折叠
摘要
Abstract
The aerodynamic characteristics of an aeroengine test chamber affect the accuracy of engine performance evaluation.To improve the flow field uniformity in a specific aeroengine test chamber,four smoothing system shcemes for the diffuser and pressure stabilization sections of the front compartment were investigated.These systems included elements such as deflector plates,conical perforated plates,flat perforated plates,honeycombs,and mesh screens,among others.Computational fluid dynamics(CFD)methods were employed to calcute the flow fields within the front compartment,incoming air pipe,and associated air valve for each proposed system.The results revealed that the valve within the incoming air pipe had some impact on the incoming flow field,resulting in uneven airflow entering the front compartment.While deflector plates and conical perforated plates reduced the mixing of the incoming flow,their effectiveness in improving the flow uniformity in test chambers with non-uniform incoming airflow was limited.Incontrast,multi-layer flat perforated plates demonstrated superior performance in flow conditioning within test chambers with non-uniform incoming airflow.These findings provide references for the design of intake smoothing systems for aeroengine test chambers.关键词
航空发动机/试验舱/进气整流/计算流体动力学/数值研究Key words
aeroengine/test chamber/intake smoothing/computational fluid dynamics/numerical study引用本文复制引用
白冰,富钰,邵钰杰,韩潇,龚洁,吕世增,赵月帅,杨波,李国华,张立明..航空发动机试验舱进气整流系统设计及数值验证[J].航天器环境工程,2025,42(2):136-143,8.
