一种新型进气畸变设计体系研究  

A new intake distortion design system for research

作　　者：崔佳航 李江红[1] 李晓宇 董素艳[1] 蔡飞超[1] 范玮[1] CUI Jiahang;LI Jianghong;LI Xiaoyu;DONG Suyan;CAI Feichao;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：《西北工业大学学报》2023年第2期363-369,共7页Journal of Northwestern Polytechnical University

基　　金：两机重大专项(J2019-I-0003-0004)资助。

摘　　要：进气畸变实验是航空发动机气动稳定性评定的重要方法之一。为克服传统设计方法逼近目标畸变图谱准确性低、实验迭代次数多等缺点,提出基于丝网间距和多孔介质映射关系,采用Fluent设计目标图谱畸变网的设计体系。设计了稳态总压测试系统,完成了畸变发生器的实物设计及风洞试验,畸变指数误差小于1.5%。试验结果表明设计体系可以高精度、高效地模拟畸变要求。The intake distortion experiment is one of the important methods for aero-engine aerodynamic stability assessment.In this paper,in order to overcome the shortcomings of traditional design methods such as low accuracy in approximating the target distortion map and many experimental iterations,a design system is proposed to design the target map distortion network using Fluent based on the mapping relationship between screen distance and porous media.Finally,the steady-state total pressure test system is designed,and the physical design of the distortion generator and wind tunnel test are completed,with the error of distortion index of less than 1.5%.The test results show that the design system can simulate the distortion requirements with high accuracy and efficiency.

关 键 词：航空发动机 畸变模拟网 FLUENT 多孔介质模型 稳态总压测试系统 

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]