基于仿真的航空发动机进气畸变系统设计方法研究  

Simulation-Based Design Method of Aero-Engine Intake Distortion System

作　　者：崔佳航 李江红[1] 李晓宇 董素艳[1] 蔡飞超[1] 范玮[1] CUI Jia-hang;LI Jiang-hong;LI Xiao-yu;DONG Su-yan;CAI Fei-chao;FAN Wei(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国飞行试验研究院,陕西西安710089

出　　处：《推进技术》2023年第5期265-272,共8页Journal of Propulsion Technology

基　　金：国家重大专项基础研究项目(J2019-Ⅰ-0003-0004)

摘　　要：进气畸变试验是航空发动机气动稳定性评定的重要方法。本文提出一种基于仿真的畸变网设计框架,克服了传统设计方法无法准确逼近目标畸变图谱、实验迭代次数多的缺点。提出了将畸变网格简化为多孔介质模型,采用CFD工具逼近目标图谱的畸变网设计方法。最终完成了300mm尺寸的畸变发生器的实物设计及风洞试验,实际的畸变指数与设计目标误差小于1%,试验结果表明设计框架可以高精度、高效地模拟畸变要求。The intake distortion test is a crucial method for determining the aerodynamic stability of an aero-engine.A simulation-based distortion grid design framework was proposed in this research to overcome the limitations of standard design methods,which could not correctly approximate the intended distortion map and re⁃quired a significant number of experimental iterations.The distortion grid design approach was provided to con⁃vert the distortion grid into a porous medium model and approximate the goal pattern using CFD tools.Finally,the 300mm size physical design and wind tunnel test of the distortion generator were completed,and the actual aberration index was less than 1%error from the design target.The test results reveal that the design framework can accurately and efficiently simulate the distortion requirements.

关 键 词：航空发动机 进气畸变 CFD 多孔介质模型 畸变发生器 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]