JZUS - Journal of Zhejiang University SCIENCE

Journal of Zhejiang University SCIENCE A

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Effects of bump parameters on hypersonic inlet starting performance

Author(s): Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG
Affiliation(s): College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
Corresponding email(s): wange_nudt@163.com
Key Words: Hypersonic inlet; Bump; Boundary layer flow; Starting performance; Large-scale separation bubble

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Abstract: Unstart is an unwanted flow phenomenon in a hypersonic inlet. When an unstart occurs, the captured airflow flowing through the engine significantly decreases with strong unsteady characteristics, which may lead to thrust loss or even combustor flameout. In this study, various bump configurations were designed to be integrated with a hypersonic inlet to improve its starting ability. A bump was defined as an integrated 3D compression surface installed upstream of the inlet entrance. The starting processes of these bump inlets were numerically simulated to investigate the effect laws and flow mechanisms of the bump parameters. Tests on bump height revealed that the starting performance could be significantly improved by increasing bump height, with the starting Mach number decreasing by 0.55 for the inlet with the highest bump. The high bump facilitates the side movement of the subsonic flow in the separation zone, which leads to a small separation bubble, thus accelerating the starting process. Further, the starting ability can be improved by designing a relatively wide bump, which results in a decline in the starting Mach number by 0.44. When the bump has the same or greater width compared with the airflow capture range, a growing spillage along the transverse direction can be formed so that the airflow in the separation bubble can be easily excluded, improving the starting ability.

鼓包构型对高超声速进气道起动性能的影响研究

作者：徐尚成，王翼，王振国，范晓樯，熊冰
机构：国防科技大学，空天科学学院，中国长沙，410073
目的：在高超声速进气道中加入鼓包构型可有效提高起动性能，然而目前对于鼓包构型对起动的影响规律及其流动机理的认识还不充分。本文旨在研究鼓包构型参数对起动性能的影响，明晰鼓包对起动过程的作用机理，进而为高超声速鼓包进气道的设计提供参考依据。
创新点：1.获得了鼓包高度和宽度对起动性能的影响规律；2.明晰了鼓包对不起动进气道大尺度分离区的重构作用，并阐释了鼓包参数影响起动性能的内在机理。
方法：1.利用基于横向压力梯度的鼓包进气道设计方法生成具有不同鼓包高度和宽度的进气道构型；2.采用数值方法计算不同的鼓包进气道在设计条件下的流场和起动过程，分析鼓包对进气道性能影响规律；3.通过分析不起动流场结构，研究鼓包对大尺度分离区的重构作用。
结论：1.鼓包可对边界层气流产生排移作用，使得进气道流量稍有下降，但总压恢复性能明显提升；2.增加鼓包高度可加速分离区内气流的横向溢流，进而提高进气道起动性能；3.为提高起动性能，应使鼓包略宽于进气道入口。

关键词组：高超声速飞行器；鼓包；边界层气流；起动性能；大尺度分离区

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鼓包构型对高超声速进气道起动性能的影响研究

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