Full Text:   <81>

Summary:  <14>

CLC number: 

On-line Access: 2022-10-20

Received: 2022-03-23

Revision Accepted: 2022-08-01

Crosschecked: 2022-10-21

Cited: 0

Clicked: 117

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Shang-cheng XU

https://orcid.org/0000-0002-0717-8392

Yi WANG

https://orcid.org/0000-0002-3657-9769

-   Go to

Article info.
Open peer comments

Journal of Zhejiang University SCIENCE A 2022 Vol.23 No.10 P.807-819

http://doi.org/10.1631/jzus.A2200155


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


Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG. Effects of bump parameters on hypersonic inlet starting performance[J]. Journal of Zhejiang University Science A, 2022, 23(10): 807-819.

@article{title="Effects of bump parameters on hypersonic inlet starting performance",
author="Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG",
journal="Journal of Zhejiang University Science A",
volume="23",
number="10",
pages="807-819",
year="2022",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A2200155"
}

%0 Journal Article
%T Effects of bump parameters on hypersonic inlet starting performance
%A Shang-cheng XU
%A Yi WANG
%A Zhen-guo WANG
%A Xiao-qiang FAN
%A Bing XIONG
%J Journal of Zhejiang University SCIENCE A
%V 23
%N 10
%P 807-819
%@ 1673-565X
%D 2022
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2200155

TY - JOUR
T1 - Effects of bump parameters on hypersonic inlet starting performance
A1 - Shang-cheng XU
A1 - Yi WANG
A1 - Zhen-guo WANG
A1 - Xiao-qiang FAN
A1 - Bing XIONG
J0 - Journal of Zhejiang University Science A
VL - 23
IS - 10
SP - 807
EP - 819
%@ 1673-565X
Y1 - 2022
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A2200155


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:高超声速飞行器;鼓包;边界层气流;起动性能;大尺度分离区

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

Reference

[1]Brito LopesAV, 2021. Advanced Modelling of Turbulent Spray Flames in Aero Gas-Turbines with Liquid Bio-Fuels. PhD Thesis, Coventry University, Coventry, UK.

[2]Brito LopesAV, EmekwuruN, BonelloB, et al., 2020. On the highly swirling flow through a confined bluff-body. Physics of Fluids, 32(5):055105.

[3]ChangJT, LiN, XuKJ, et al., 2017. Recent research progress on unstart mechanism, detection and control of hypersonic inlet. Progress in Aerospace Sciences, 89:1-22.

[4]CollissSP, BabinskyH, NüblerK, et al., 2014. Joint experimental and numerical approach to three-dimensional shock control bump research. AIAA Journal, 52(2):‍436-446.

[5]CurranET, 2001. Scramjet engines: the first forty years. Journal of Propulsion and Power, 17(6):1138-1148.

[6]DevaraMKK, JuturP, RaoSMV, et al., 2020. Experimental investigation of unstart dynamics driven by subsonic spillage in a hypersonic scramjet intake at Mach 6. Physics of Fluids, 32(2):026103.

[7]ErdemE, KontisK, 2010. Numerical and experimental investigation of transverse injection flows. Shock Waves, 20(2):103-118.

[8]HamstraJW, SylvesterTG, 1998. System and Method for Diverting Boundary Layer Air. US Patent 5779189.

[9]ImS, BaccarellaD, McGannB, et al., 2016. Unstart phenomena induced by mass addition and heat release in a model scramjet. Journal of Fluid Mechanics, 797:604-629.

[10]KantrowitzA, DonaldsonCD, 1945. Preliminary Investigation of Supersonic Diffusers. NACA Wartime Report No. L5D20, National Advisory Committee for Aeronautics, Washington, USA.

[11]KimSD, 2009. Aerodynamic design of a supersonic inlet with a parametric bump. Journal of Aircraft, 46(1):198-202.

[12]KimSD, SongDJ, 2007. A numerical analysis on three-dimensional flow field in a supersonic bump-type inlet. Journal of Mechanical Science and Technology, 21(2):327-335.

[13]LiLQ, HuangW, YanL, et al., 2018. Mixing improvement induced by the combination of a micro-ramp with an air porthole in the transverse gaseous injection flow field. International Journal of Heat and Mass Transfer, 124:109-123.

[14]LiuJ, YuanHC, WangYF, et al., 2017. Unsteady supercritical/critical dual flowpath inlet flow and its control methods. Chinese Journal of Aeronautics, 30(6):1877-1884.

[15]LiuJB, FanXQ, TaoY, et al., 2019. Experimental and numerical study on the local unstart mechanism of hypersonic inlet. Acta Astronautica, 160:216-221.

[16]MahoneyJJ, 1990. Inlets for Supersonic Missiles. American Institute of Aeronautics and Astronautics, Washington, USA.

[17]MolderS, TimofeevEV, TahirRB, 2004. Flow starting in high compression hypersonic air inlets by mass spillage. Proceedings of the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[18]ReardonJP, SchetzJA, LoweKT, 2021. Computational analysis of unstart in variable-geometry inlet. Journal of Propulsion and Power, 37(4):564-576.

[19]RodriguezCG, 2003. Computational fluid dynamics analysis of the central institute of aviation motors/NASA scramjet. Journal of Propulsion and Power, 19(4):547-555.

[20]SimonPC, BrownDW, HuffRG, 1957. Performance of External-Compression Bump Inlet at Mach Number of 1.5 to 2.0. NACA RM E56L19, National Advisory Committee for Aeronautics, Washington, USA.

[21]SuWY, ChenY, ZhangFR, et al., 2018. Control of pseudo-shock oscillation in scramjet inlet-isolator using periodical excitation. Acta Astronautica, 143:147-154.

[22]SvenssonM, 2008. A CFD Investigation of a Generic Bump and Its Application to a Diverterless Supersonic Inlet. MS Thesis, Swedish Defense Research Agency, Stockholm, Sweden.

[23]SziroczakD, SmithH, 2016. A review of design issues specific to hypersonic flight vehicles. Progress in Aerospace Sciences, 84:1-28.

[24]TengJ, YuanHC, 2015. Variable geometry cowl sidewall for improving rectangular hypersonic inlet performance. Aerospace Science and Technology, 42:128-135.

[25]TillotsonBJ, LothE, DuttonJC, et al., 2009. Experimental study of a Mach 3 bump-compression flowfield. Journal of Propulsion and Power, 25(3):545-554.

[26]VolandRT, AuslenderAH, SmartMK, et al., 1999. CIAM/NASA Mach 6.5 scramjet flight and ground test. Proceedings of the 9th International Space Planes and Hypersonic Systems and Technologies Conference.

[27]WalkerS, RodgersF, EspositaA, 2005. The hypersonic collaborative Australia/United States experiment (HyCAUSE). Proceedings of the AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference.

[28]WalkerS, RodgersF, PaullA, et al., 2008. HyCAUSE flight test program. Proceedings of the 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.

[29]WangY, LiangJH, FanXQ, et al., 2009. Investigation on the unstarted flowfield of a three-dimensional sidewall compression hypersonic inlet. Proceedings of the 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference.

[30]XieWZ, GuoRW, 2008. A ventral diverterless high offset S-shaped inlet at transonic speeds. Chinese Journal of Aeronautics, 21(3):207-214.

[31]XuSC, WangY, WangZG, et al., 2017. The design and analysis of bump in high speed supersonic flow. Proceedings of the 21st AIAA International Space Planes and Hypersonics Technologies Conference.

[32]XuSC, WangY, WangZG, et al., 2019. Design and analysis of a hypersonic inlet with an integrated bump/forebody. Chinese Journal of Aeronautics, 32(10):2267-2274.

[33]XuSC, WangY, WangZG, et al., 2022. Design method for hypersonic bump inlet based on transverse pressure gradient. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 23(6):479-494.

[34]YuZH, HuangGP, XiaC, 2018. Inverse design and Mach 6 experimental investigation of a pressure controllable bump. Aerospace Science and Technology, 81:204-212.

[35]YuZH, HuangGP, XiaC, 2020. 3D inverse method of characteristics for hypersonic bump-inlet integration. Acta Astronautica, 166:11-22.

[36]YuanYC, LiuFZ, WangX, et al., 2021. Design and analysis of a supersonic axisymmetric inlet based on controllable bleed slots. Aerospace Science and Technology, 118:107008.

[37]ZhangBH, ZhaoXY, LiuJ, 2020. Effects of bleed hole size on supersonic boundary layer bleed mass flow rate. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(8):652-662.

Open peer comments: Debate/Discuss/Question/Opinion

<1>

Please provide your name, email address and a comment





Journal of Zhejiang University-SCIENCE, 38 Zheda Road, Hangzhou 310027, China
Tel: +86-571-87952783; E-mail: cjzhang@zju.edu.cn
Copyright © 2000 - 2022 Journal of Zhejiang University-SCIENCE