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.
概要
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.
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Acknowledgments
This work is supported by the National Natural Science Foundation of China (No. 12102470) and the Hunan Provincial Innovation Foundation for Postgraduate (No. CX20200082), China.
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Shang-cheng XU, Yi WANG, and Zhen-guo WANG designed the research. Shang-cheng XU and Bing XIONG processed the corresponding data. Shang-cheng XU wrote the first draft of the manuscript. Xiao-qiang FAN and Bing XIONG helped to organize the manuscript. Yi WANG revised and edited the final version.
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Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, and Bing XIONG declare that they have no conflict of interest.
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Xu, Sc., Wang, Y., Wang, Zg. et al. Effects of bump parameters on hypersonic inlet starting performance. J. Zhejiang Univ. Sci. A 23, 807–819 (2022). https://doi.org/10.1631/jzus.A2200155
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DOI: https://doi.org/10.1631/jzus.A2200155