CLC number:
On-line Access: 2022-10-20
Received: 2022-03-23
Revision Accepted: 2022-08-01
Crosschecked: 2022-10-21
Cited: 0
Clicked: 699
Citations: Bibtex RefMan EndNote GB/T7714
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,in press.Frontiers of Information Technology & Electronic Engineering,in press.https://doi.org/10.1631/jzus.A2200155 @article{title="Effects of bump parameters on hypersonic inlet starting performance", %0 Journal Article TY - JOUR
鼓包构型对高超声速进气道起动性能的影响研究机构: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: 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. Journal of Zhejiang University-SCIENCE, 38 Zheda Road, Hangzhou
310027, China
Tel: +86-571-87952783; E-mail: cjzhang@zju.edu.cn Copyright © 2000 - 2024 Journal of Zhejiang University-SCIENCE |
Open peer comments: Debate/Discuss/Question/Opinion
<1>