Full Text:   <2310>

Summary:  <1636>

CLC number: V231.3

On-line Access: 2024-08-27

Received: 2023-10-17

Revision Accepted: 2024-05-08

Crosschecked: 2020-08-06

Cited: 0

Clicked: 3334

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Wen-xin Hou

https://orcid.org/0000-0002-1322-4359

Jun-tao Chang

https://orcid.org/0000-0003-0019-2068

-   Go to

Article info.
Open peer comments

Journal of Zhejiang University SCIENCE A 2020 Vol.21 No.8 P.614-635

http://doi.org/10.1631/jzus.A2000042


Experimental study and analysis of shock train self-excited oscillation in an isolator with background waves


Author(s):  Wen-xin Hou, Jun-tao Chang, Chen Kong, Wen Bao, Laurent Dala

Affiliation(s):  School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China; more

Corresponding email(s):   changjuntao@hit.edu.cn

Key Words:  Self-excited oscillation, Background waves, Asymmetrical structure, Source of perturbation


Wen-xin Hou, Jun-tao Chang, Chen Kong, Wen Bao, Laurent Dala. Experimental study and analysis of shock train self-excited oscillation in an isolator with background waves[J]. Journal of Zhejiang University Science A, 2020, 21(8): 614-635.

@article{title="Experimental study and analysis of shock train self-excited oscillation in an isolator with background waves",
author="Wen-xin Hou, Jun-tao Chang, Chen Kong, Wen Bao, Laurent Dala",
journal="Journal of Zhejiang University Science A",
volume="21",
number="8",
pages="614-635",
year="2020",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A2000042"
}

%0 Journal Article
%T Experimental study and analysis of shock train self-excited oscillation in an isolator with background waves
%A Wen-xin Hou
%A Jun-tao Chang
%A Chen Kong
%A Wen Bao
%A Laurent Dala
%J Journal of Zhejiang University SCIENCE A
%V 21
%N 8
%P 614-635
%@ 1673-565X
%D 2020
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2000042

TY - JOUR
T1 - Experimental study and analysis of shock train self-excited oscillation in an isolator with background waves
A1 - Wen-xin Hou
A1 - Jun-tao Chang
A1 - Chen Kong
A1 - Wen Bao
A1 - Laurent Dala
J0 - Journal of Zhejiang University Science A
VL - 21
IS - 8
SP - 614
EP - 635
%@ 1673-565X
Y1 - 2020
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A2000042


Abstract: 
A study of shock train self-excited oscillation in an isolator with background waves was implemented through a wind tunnel experiment. Dynamic pressure data were captured by high-frequency pressure measurements and the flow field was recorded by the high-speed Schlieren technique. The shock train structure was mostly asymmetrical during self-excited oscillation, regardless of its oscillation mode. We found that the pressure discontinuity caused by background waves was responsible for the asymmetry. On the wall where the pressure at the leading edge of the shock train was lower, a large separation region formed and the shock train deflected toward to the other wall. The oscillation mode of the shock train was related to the change of wall pressure in the oscillation range of its leading edge. The oscillation range and oscillation intensity of the shock train leading edge were affected by the wall pressure gradient induced by background waves. When located in a negative pressure gradient region, the oscillation of the leading edge strengthened; when located in a positive pressure gradient region, the oscillation weakened. To find out the cause of self-excited oscillation, correlation and phase analyses were performed. The results indicated that the instability of the separation region induced by the leading shock was the source of perturbation that caused self-excited oscillation, regardless of the oscillation mode of the shock train.

带有背景波系的隔离段内激波串自激振荡的实验研究与分析

目的:隔离段内存在背景波系时,激波串在自激振荡过程中会出现三种振荡模式,并表现出非对称结构. 本文旨在研究背景波系是如何引起激波串的非对称结构以及背景波系对振荡特性的影响,并探究自激振荡的扰动来源.
创新点:1. 从激波串结构和振荡特性两个方面揭示背景波系对激波串自激振荡的影响; 2. 获得引起激波串自激振荡的扰动来源.
方法:1. 通过实验分析,结合激波极曲线,研究背景波系引起的压力间断对激波串结构的影响; 2. 结合实验获得的激波串振荡特性以及数值模拟得到的壁面压力梯度,分析背景波系引起的压力梯度对自激振荡的影响; 3. 通过对壁面压力进行相关性分析和相位分析,获得自激振荡扰动的来源.
结论:1. 背景波系引起的压力间断导致了激波串的非对称结构; 2. 背景波系引起的壁面压力梯度影响激波串前缘的振荡范围和振荡强度; 3. 在带有背景波系的隔离段内,引起自激振荡的扰动来源于前缘激波产生的分离区内.

关键词:自激振荡; 背景波系; 非对称结构; 扰动源

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

Reference

[1]Cai JH, Zhou J, Liu SJ, et al., 2017. Effects of dynamic backpressure on shock train motions in straight isolator. Acta Astronautica, 141:237-247.

[2]Carroll BF, Dutton JC, 1990. Characteristics of multiple shock wave/turbulent boundary-layer interactions in rectangular ducts. Journal of Propulsion and Power, 6(2):186-193.

[3]Fiévet R, Koo H, Raman V, et al., 2017. Numerical investigation of shock-train response to inflow boundary-layer variations. AIAA Journal, 55(9):2888-2901.

[4]Geerts JS, Yu KH, 2016. Shock train/boundary-layer interaction in rectangular isolators. AIAA Journal, 54(11):3450-3464.

[5]Gnani F, Zare-Behtash H, Kontis K, 2016. Pseudo-shock waves and their interactions in high-speed intakes. Progress in Aerospace Sciences, 82:36-56.

[6]Hou WX, Chang JT, Xie ZQ, et al., 2020. Behavior and flow mechanism of shock train self-excited oscillation influenced by background waves. Acta Astronautica, 166:29-40.

[7]Huang W, Wang ZG, Pourkashanian M, et al., 2011. Numerical investigation on the shock wave transition in a three-dimensional scramjet isolator. Acta Astronautica, 68(11-12):1669-1675.

[8]Hunt RL, Gamba M, 2018. Shock train unsteadiness characteristics, oblique-to-normal transition, and three-dimensional leading shock structure. AIAA Journal, 56(4):1569-1587.

[9]Ikui T, Matsuo K, Nagai M, et al., 1974. Oscillation phenomena of pseudo-shock waves. Bulletin of JSME, 17(112):1278-1285.

[10]Jiao XL, Chang JT, Wang ZQ, et al., 2016. Investigation of hypersonic inlet pulse-starting characteristics at high Mach number. Aerospace Science and Technology, 58: 427-436.

[11]Li N, Chang JT, Xu KJ, et al., 2017. Prediction dynamic model of shock train with complex background waves. Physics of Fluids, 29(11):116103.

[12]Li N, Chang JT, Xu KJ, et al., 2018. Oscillation of the shock train in an isolator with incident shocks. Physics of Fluids, 30(11):116102.

[13]Liao L, Yan L, Huang W, et al., 2018. Mode transition process in a typical strut-based scramjet combustor based on a parametric study. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 19(6):431-451.

[14]Lu L, Wang Y, Fan XQ, et al., 2018. Numerical investigation of shock train unsteady movement in a mixing duct. Aerospace Science and Technology, 81:375-382.

[15]Matsuo K, Miyazato Y, Kim HD, 1999. Shock train and pseudo-shock phenomena in internal gas flows. Progress in Aerospace Sciences, 35(1):33-100.

[16]Raj NOP, Venkatasubbaiah K, 2012. A new approach for the design of hypersonic scramjet inlets. Physics of Fluids, 24(8):086103.

[17]Shi W, Chang JT, Ma JC, et al., 2019a. Path dependence characteristic of shock train in a 2D hypersonic inlet with variable background waves. Aerospace Science and Technology, 86:650-658.

[18]Shi W, Chang JT, Zhang JL, et al., 2019b. Numerical investigation on the forced oscillation of shock train in hypersonic inlet with translating cowl. Aerospace Science and Technology, 87:311-322.

[19]Smirnov NN, Betelin VB, Shagaliev RM, et al., 2014. Hydrogen fuel rocket engines simulation using LOGOS code. International Journal of Hydrogen Energy, 39(20):10748-10756.

[20]Smirnov NN, Betelin VB, Nikitin VF, et al., 2015. Accumulation of errors in numerical simulations of chemically reacting gas dynamics. Acta Astronautica, 117:338-355.

[21]Su WY, Zhang KY, 2013. Back-pressure effects on the hypersonic inlet-isolator pseudoshock motions. Journal of Propulsion and Power, 29(6):1391-1399.

[22]Su WY, Chen Y, Zhang FR, et al., 2018. Control of pseudo-shock oscillation in scramjet inlet-isolator using periodical excitation. Acta Astronautica, 143:147-154.

[23]Sugiyama H, Takeda H, Zhang JP, et al., 1988. Locations and oscillation phenomena of pseudo-shock waves in a straight rectangular duct. JSME International Journal Ser. 2, Fluids Engineering, Heat Transfer, Power, Combustion, Thermophysical Properties, 31(1):9-15.

[24]Sugiyama H, Tsujiguchi Y, Honma T, 2008. Structure and oscillation phenomena of pseudo-shock waves in a straight square duct at Mach 2 and 4. Proceedings of the 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, p.2646.

[25]Tam CJ, Hsu KY, Hagenmaier M, et al., 2013. Studies of inlet distortion in a direct-connect axisymmetric scramjet isolator. Journal of Propulsion and Power, 29(6):1382-1390.

[26]Tan HJ, Sun S, Huang HX, 2012. Behavior of shock trains in a hypersonic inlet/isolator model with complex background waves. Experiments in Fluids, 53(6):1647-1661.

[27]Wagner JL, Yuceil KB, Valdivia A, et al., 2009. Experimental investigation of unstart in an inlet/isolator model in Mach 5 flow. AIAA Journal, 47(6):1528-1542.

[28]Waltrup PJ, Billig FS, 1973. Structure of shock waves in cylindrical ducts. AIAA Journal, 11(10):1404-1408.

[29]Wang CP, Cheng C, Cheng KM, et al., 2018. Unsteady behavior of oblique shock train and boundary layer interactions. Aerospace Science and Technology, 79:212-222.

[30]Wen X, Liu J, Li J, et al., 2019. Design and numerical simulation of a clamshell-shaped inlet cover for air-breathing hypersonic vehicles. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(5):347-357.

[31]Xing F, Ruan C, Huang Y, et al., 2017. Numerical investigation on shock train control and applications in a scramjet engine. Aerospace Science and Technology, 60:162-171.

[32]Xiong B, Wang ZG, Fan XQ, et al., 2017a. Experimental study on the flow separation and self-excited oscillation phenomenon in a rectangular duct. Acta Astronautica, 133: 158-165.

[33]Xiong B, Fan XQ, Wang Y, et al., 2017b. Back-pressure effects on unsteadiness of separation shock in a rectangular duct at Mach 3. Acta Astronautica, 141:248-254.

[34]Xu KJ, Chang JT, Zhou WX, et al., 2016. Mechanism and prediction for occurrence of shock-train sharp forward movement. AIAA Journal, 54(4):1403-1412.

[35]Xu KJ, Chang JT, Zhou WX, et al., 2017. Mechanism of shock train rapid motion induced by variation of attack angle. Acta Astronautica, 140:18-26.

[36]Xu KJ, Chang JT, Li N, et al., 2018. Experimental investigation of mechanism and limits for shock train rapid forward movement. Experimental Thermal and Fluid Science, 98:336-345.

[37]Yamane R, Kondo E, Tomita Y, et al., 1984. Vibration of pseudo-shock in straight duct: 1st report, fluctuation of static pressure. Bulletin of JSME, 27(229):1385-1392.

[38]Zhang TT, Wang ZG, Huang W, et al., 2019. The overall layout of rocket-based combined-cycle engines: a review. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(3):163-183.

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 - 2024 Journal of Zhejiang University-SCIENCE