超声速可调进气道内流双解现象及其节流特性  

Dual solution internal flow phenomenon and throttling characteristics of a supersonic variable inlet

作　　者：金毅 孙姝[2] 郭赟杰 谭慧俊 张悦 JIN Yi;SUN Shu;GUO Yunjie;TAN Huijun;ZHANG Yue(Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏省航空动力系统重点实验室,南京210016 [2]南京航空航天大学民航学院,南京211106

出　　处：《航空学报》2023年第7期77-86,共10页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(U20A2070,12025202)。

摘　　要：为研究超声速可调进气道喉道调节过程中的内流结构及节流特性,设计了工作马赫数范围为0~4的超声速可调进气道,在来流马赫数为2.9的风洞中借助高速纹影观测系统和动态压力测量系统开展了试验研究。结果表明当内收缩比(ICR)为1.79时,进气道通流流场存在设计和非设计流态的内流双解现象。其中,在设计流态下进气道内通道中的波系结构正常建立;而在非设计流态下进气道内收缩段中存在局部分离诱导的复杂波系结构,导致其整体压升高于设计流态,并存在宽频、低频的小幅振荡。此外设计和非设计流态下进气道的下游节流性能相当,其临界堵塞度分别为42.4%和41.7%,临界压比分别为15.8和16.0。在两类流态的下游节流过程中扰动均以结尾斜激波串的形式向上游传播,且临界状态下激波串头波刚好位于喉道附近,但两类流态的结尾激波串在空间分布特征和振荡特性上均存在明显区别。A supersonic variable inlet with an operating Mach number ranging from 0–4 was designed to investigate its internal flow structures and throttling characteristics.All tests were conducted in the wind tunnel at a freestream Mach number of 2.9 with the aid of the high-speed schlieren and dynamic pressure data-acquisition systems.The results show that when the Internal Contraction Ratio(ICR)is 1.79,the unthrottled internal flowfield of the inlet has the dual solution of designed and undesigned flow states.In the designed flow state,the wave system in the inlet internal duct is normally established;while in the undesigned flow state,there is a complex wave system induced by local separa⁃tion in the inlet internal contraction part,resulting in its overall pressure rise higher than that of the designed flow state and the presence of broadband,low-frequency small-amplitude oscillations.In addition,the inlet downstream throttling performance in the designed and undesigned flow states is comparable with critical throttling ratios of 42.4%and 41.7%and critical pressure ratios of 15.8 and 16.0,respectively.During the downstream throttling process in both types of flow states,the disturbance propagates upstream in the form of an oblique terminal shock train,and the head wave of the shock train in the critical state is located just near the throat station.However,apparent differences exist in the spatial distribution characteristics and oscillatory features of the terminal shock train of the two flow states.

关 键 词：超声速可调进气道 双解现象 节流特性 激波串 风洞试验 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]