摘要
为确保超声速Bump进气道在全包线范围内与发动机高效匹配,探讨了提升其稳定工作裕度的主导机制。以四唇缘前掠外罩Bump进气道为研究对象,分析了其在设计马赫数下从超临界到亚临界工况的三维流动结构演化。研究结果表明,在小流量(或高反压)条件下,前掠外罩与锥导鼓包相结合的进气道压缩面上,正激波/边界层干扰产生三维分离涡流,并将涡流排移至进口外部。相比之下,相同前掠外罩与平面楔组合的进气道在小流量条件下,分离流呈现出“准二维”流态且大部分被吸入至进气道内部,其稳定裕度较鼓包进气道窄。因此,产生三维分离涡流,并将其排移出进口是提升Bump进气道气动性能、拓宽稳定工作裕度的核心机制。
To ensure the efficient matching of the supersonic Bump inlet with the engine across the entire flight envelope,this paper explores the dominant mechanism for enhancing its stable operational margin.Taking the four-lip forward-swept cowl Bump inlet as the subject of study,the evolution of the three-dimensional flow structure from supercritical to subcritical conditions at the designed Mach number is analyzed.The research findings indicate that under low mass flow(or high back pressure)conditions,the interaction between the normal shock and the boundary layer on the compression surface of the inlet,which combines a forward-swept cowl and a conical bump,generates a three-dimensional separation vortex that is expelled to the exterior of the inlet entrance.In contrast,an inlet with the same forward-swept cowl combined with a flat wedge experiences a“quasi-two-dimensional”flow separation under low mass flow conditions,with most of the separated flow being ingested into the inlet to result in a narrower stable margin as compared with the Bump inlet.Therefore,the generation of a three-dimensional separation vortex and its expulsion out of the entrance of the duct is the core mechanism for enhancing the aerodynamic performance of the Bump inlet and broadening its stable operational margin.
作者
朱宇
程健慧
陈诚
黄河峡
谭慧俊
Yu ZHU;Jianhui CHENG;Cheng CHEN;Hexia HUANG;Huijun TAN(AVIC Shenyang Aircraft Design and Research Institute,Shenyang 110035,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空学报》
CSCD
北大核心
2024年第24期192-202,共11页
Acta Aeronautica et Astronautica Sinica
基金
先进航空动力创新工作站项目(HKCX2022-01-027,HKCX202-02-005)
国家自然科学基金(12272177,U20A2070,12172175)
青年托举人才工程项目(2021-JCJQ-QT-064)。
关键词
Bump进气道
激波/边界层干扰
分离流
进发匹配
流动控制
Bump inlet
shock wave/boundary layer interaction
separated flow
inlet-engine matching
flow control
