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

作　　者：白冰 邵钰杰 韩潇[1] 龚洁[1] 吕世增[1] 赵月帅[1] 杨波 李国华 张立明 富钰 BAI Bing;SHAO Yujie;HAN Xiao;GONG Jie;LÜShizeng;ZHAO Yueshuai;YANG Bo;LI Guohua;ZHANG Liming;FU Yu(Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《航天器环境工程》2025年第2期136-143,共8页Spacecraft Environment Engineering

摘　　要：航空发动机试验舱的气动特性影响发动机性能评估准确性。为提高某型航空发动机试验舱的流场均匀性,文章针对试验舱前舱的扩压段和稳压段,设计了4套不同的整流系统组合方案,包括折流板、锥形多孔板、平面多孔板、蜂窝器和阻尼网等元素。应用计算流体动力学(CFD)方法对各个方案的前舱、来流管道及来流阀门的流场进行计算。结果表明,来流管道中的阀门对来流流场造成了一定影响,导致进入前舱的气流不均匀;折流板和锥形多孔板减小了气流的掺混作用,对不均匀来流试验舱的整流效果有限;而多层平面多孔板在不均匀来流试验舱的整流方面表现更为优异。以上研究结果可为试验舱整流系统的设计提供参考。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 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程] V231.3