非均匀来流的马赫数可控内收缩进气道设计  

Design of inward turning inlet with controlled Mach number under non-uniform inflow

作　　者：李永洲 孙迪 王仁华 张堃元[3] LI Yongzhou;SUN Di;WANG Renhua;ZHANG Kunyuan(College of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China;AECC Aero Engine Control System Institute,Wuxi 214063,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063 [2]中国航发控制系统研究所,无锡214063 [3]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空学报》2023年第12期157-169,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11702205);江西省“双千计划”创新领军人才项目;航空发动机热环境与热结构重点实验室开放基金(CEPE2022005);重庆市自然科学基金面上项目(cstc2020jcyj-msxmX0823)。

摘　　要：为了满足腹部进气布局高超声速飞行器乘波前体与进气道一体化设计要求,发展了一种来流非均匀的马赫数分布可控内收缩进气道设计方法。在来流马赫数和壁面马赫数分布规律同时给定的前提下,通过有旋特征线法反设计轴对称基准流场,然后结合流线追踪技术生成圆形进口内收缩进气道,同时与传统基于均匀来流设计的内收缩进气道进行对比。数值仿真结果表明:非均匀来流的基准流场结构与设计预期一致,可以实现对整个流场的马赫数分布控制,且其压缩效率高于传统均匀来流设计的基准流场。设计点时非均匀来流设计的进气道保持了基准流场的波系结构并实现了全流量捕获。有黏时非均匀来流设计的进气道总体性能较高且高于同样来流条件下均匀来流设计的进气道。该设计方法可行,为高超声速乘波前体与进气道一体化设计提供了一种新途径。A design method of the inward turning inlet with controlled Mach number distribution under non-uniform inflow is proposed to meet the integrated design requirements of waverider and inlet of the hypersonic vehicle with the abdominal intake layout.The axisymmetric basic flow field is designed inversely by the rotational method of characteristics under the conditions that the Mach number distribution of the inflow and the wall are given at the same time.The inward turning inlet with the circular intake is designed by the streamline tracing technology and compared with the tra ditional inward turning inlet based on the uniform inflow.The numerical simulation results show that the basic flow field structure of the non-uniform inflow is consistent with expectation,which can control the Mach number distribution of the entire flow field,and its compression efficiency is higher than that of the traditional uniform inflow.The inlet with nonuniform inflow can maintain the wave structure of the basic flow field and capture the full flow at the deign point.The overall performance of the inlet with non-uniform inflow under viscous conditions is satisfactory and higher than that of the inlet with uniform inflow under the same inflow condition.Therefore,the design method is feasible and provides an innovative approach for hypersonic foredody/inlet integrated design.

关 键 词：高超声速进气道 非均匀来流 基准流场 马赫数 一体化设计 流线追踪 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]