核心机进气总压畸变试验仿真与验证
The numerical simulation and test verification of the inlet total pressure distortion of a core aero-engine
吴志昌 1李运南 1于之帅 1朱哲民1
作者信息
- 1. 中国航发沈阳发动机研究所,沈阳 110015
- 折叠
摘要
某型核心机首次开展进气总压畸变试验,为了在正式试验前预知核心机进口前气动交界面稳态总压分布图谱,通过商用软件模拟了不同进气状态和板位条件下气动交界面的稳态总压分布,并与试验结果进行了对比.结果表明:气动交界面8支稳态总压探针测得的周向总压分布与仿真计算结果趋势一致,最大误差为2.1%,出现在计算状态换算转速为95%、板位为24%的第4支探针处,验证了数值计算方法的准确性.为开展型号总压畸变试验的设计与验证提供了理论和技术基础,并可为后续其他型号发动机进气总压畸变试验提供支持.
Abstract
The inlet total pressure distortion test was carried out on a core aero-engine for the first time.Before the formal test,the total pressure distribution of the aerodynamic interface under different inlet states and positions was simulated by commercial software and the results were compared with the experiment.The results show that the distribution of the circular total pressure distortion measured by the 8 probes of the aerodynamic interface is consistent with the simulation results,with a maximum error of 2.1%,which occurs at the 4th probe in the calculated states 95%,plate position 24%.The correctness of numerical calculation method was verified,which provided reference for the design and verification of inlet total pressure distortion tests of models,as well as support for the following inlet total pressure distortion test of other models.
关键词
航空发动机/核心机/总压畸变/气动流场/仿真计算/试验验证Key words
aero-engine/core aero-engine/total pressure distortion/aerodynamic flow field/numerical simulation/experimental validation引用本文复制引用
出版年
2024
NETL
NSTL
万方数据