Numerical Simulation of the Effect of Curved Surface Reflectors on the External Flow Field of Pulse Detonation Engine

doi:10.12382/bgxb.2022.0261

Abstract

Abstract:

To explore a technical way to effectively suppress the propagation of high-power detonation noise generated by a pulse detonation engine to the key parts of the engine head, the external flow field of pulse detonation engine equipped with three kinds of reflectors,which are ellipsoidal reflector,parabolic reflector and conical reflector,are numerically simulated by using the space-time conservation element and solution element method.The results show that the three types of reflectors have varying effects on the detonation noise due to their distinct reflection characteristics onthe rotating surface.The ellipsoidal reflector converges the reflected wave towards the axis of the reflector.The parabolic reflector approximately parallelizes the reflected waves downstream, whilethe conical reflector does not produce the reflected wave lagging behind the direct wave,which strengthens the direct wave and propagates downstream together.

Key words: pluse detonation engine, detonation noise, curved surface reflector, reflected wave

KANG Yang, LI Ning, HUANG Xiaolong, ZHANG Junshan, WENG Chunsheng. Numerical Simulation of the Effect of Curved Surface Reflectors on the External Flow Field of Pulse Detonation Engine[J]. Acta Armamentarii, 2023, 44(7): 1966-1977.

Figures/Tables 10

Fig.1 Two-phase PDE axisymmetric computational model

Table 1 Comparison of computational results and C-J theoretical values

参数	理论C-J值	计算值	相对误差/%
压力/MPa	1.89	2.01	6.35
波速/(m·s^-1)	1792.7	1630.3	9.06

Fig.2 Grid independence validation

Fig.3 Comparison of computational and experimental results

Fig.4 Pressure contours of PDE external flow field

Fig.5 Computational models of three reflectors

Fig.6 Pressure contours of PDE with ellipsoidal reflector

Fig.7 Pressure contours of PDE with parabolic reflector

Fig.8 Pressure contours of PDE with conical reflector

Fig.9 Pressure histories at different monitoring points

References 23

[1]	BUYAKOFU V, MATSUOKA K, MATSUYAMA K, et al. Flight Demonstration of detonation engine system using sounding rocket S-520-31:performance of pulse detonation engine[C]//Proceedings of AIAA SCITECH 2022 Forum.San Diego,CS, US: CA & Virtual, 2022:0233.
[2]	郭琦, 李兆庆. 国外脉冲爆震发动机技术研究[J]. 燃气涡轮试验与研究, 2005, 18(3):59-62.
	GUO Q, LI Z Q. Review of research on pulsed detonation engines[J]. Gas Turbine Experiment and Research, 2005, 18(3):59-62. (in Chinese)
[3]	HUANG X L, LI N, WENG C S. Physical characteristics of detonation noise from multi-tube pulse detonation engine[J]. Chinese Journal of Acoustics, 2021, 40(3):378-388.
[4]	ANAND V, GLASER A, GUTMARK E. Acoustic characterization of pulse detonation combustors[J]. AIAA Journal, 2018, 56(7):2806-2815. doi: 10.2514/1.J056204 URL
[5]	XU G Y, WANG C G, ZHU Y F, et al. Study on influence of dimeter on detonation acoustics characteristics of pulse detonation engine[J/OL]. International Journal of Turbo & Jet Engines, 2020 [2021-07-02]. https://www.degruyter.com/document/doi/10.1515/tjj-2020-0003/html.
[6]	XU G Y, LI B X, LI H Y, et al. Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine[J/OL]. International Journal of Turbo & Jet Engines, 2021[2021-06-04].https://www.degruyter.com/document/doi/10.1515/tjeng-2021-0016/html.
[7]	HUANG X L, LI N, KANG Y, et al. Analysis on impulse characteristics of pulse detonation engine with nozzles[J/OL]. International Journal of Turbo & Jet-Engines, 2021[2021-10-07].https://www.degruyter.com/document/doi/10.1515/tjeng-2021-0050/html.
[8]	黄孝龙, 许桂阳, 翁春生, 等. 脉冲爆轰发动机爆轰噪声场区域划分及其数值模拟[J]. 兵工学报, 2015, 36(10):1855-1860. doi: 10.3969/j.issn.1000-1093.2015.10.005
	HUANG X L, XU G Y, WENG C S, et al. The classification and numerical calculation of noise propagation outside pulse detonation engine[J]. ActaArmamentarii, 2015, 36(10):1855-1860. (in Chinese)
[9]	KANG Y, LI N, WENG C S, et al. Acoustic characteristics of pulse detonation engine with ellipsoidal reflector[J]. Chinese Physics B, 2018, 27(10):104703. doi: 10.1088/1674-1056/27/10/104703
[10]	康杨, 李宁, 黄孝龙, 等. 基于环形喷管的脉冲爆轰发动机爆轰声波声学特性[J]. 兵工学报, 2022, 43(5):1075-1082. doi: 10.12382/bgxb.2021.0241
	KANG Y, LI N, HUANG X L, et al. Acousticcharacteristics of pulse detonation engine with annular nozzle[J]. Acta Armamentarii, 2022, 43(5):1075-1082. (in Chinese)
[11]	HYUN J, KIM H A. Transient level-set topology optimization of a planar acoustic lens working with short-duration pulse[J]. The Journal of the Acoustical Society of America, 2021, 149(5):3010-3026. doi: 10.1121/10.0004819 URL
[12]	刘小龙, 张群飞, 雷开卓. 水下强声源的多电极阵列聚束特性[J]. 高压物理学报, 2017, 31(2):175-181.
	LIU X L, ZHANG Q F, LEI K Z. Multi-Electrode array bunching characteristics of underwater intense sound source[J]. Chinese Journal of High Pressure Physics, 2017, 31(2):175-181. (in Chinese)
[13]	ZHOU Y, ZHONG P. The effect of reflector geometry on the acoustic field and bubble dynamics produced by an electrohydraulic shock wave lithotripter[J]. The Journal of the Acoustical Society of America, 2006, 119(6):3625-3636. doi: 10.1121/1.2195074 URL
[14]	BOESCH H E, REIFF C G, BENWELL B T, et al. Experimental and theoretical considerations for tailoring acoustic pulses from multi-shocktubes sources[C]//Proceedings of the 38th Aerospace Sciences Meeting & Exhibit.Reno,NV,US:AIAA, 2000:0610.
[15]	WANG G, ZHANG D L, LIU K X, et al. An improved CE/SE scheme for numerical simulation of gaseous and two-phase detonations[J]. Computers & Fluids, 2010, 39(1):168-177. doi: 10.1016/j.compfluid.2009.07.010 URL
[16]	LIN L, WENG C S, CHEN Q, et al. Study on the effects of ionization seeds on pulse detonation characteristics[J]. Aerospace Science and Technology, 2017, 71:128-135. doi: 10.1016/j.ast.2017.09.015 URL
[17]	WANG F, WENG C S, WU Y W, et al. Effects of total pressures and equivalence ratios on kerosene/air rotating detonation engines using a paralleling CE/SE method[J]. Defence Technology, 2021, 17(6):1805-1816. doi: 10.1016/j.dt.2020.09.015
[18]	RANGER A A, NICHOLLS J A. Aerodynamic shattering of liquid drops[J]. AIAA Journal, 1969, 7(2):285-290. doi: 10.2514/3.5087 URL
[19]	EIDELMAN S, BURCAT A. Evolution of a detonation wave in a cloud of fuel droplet: Part I. Influence of igniting explosion[J]. AIAA Journal, 1980, 18(9):1103-1109. doi: 10.2514/3.7711 URL
[20]	MA D H, WENG C S. Application of two-dimensional viscous CE/SE method in calculation of two-phase detonation[J]. Journal of China Ordnance, 2010, 6(1):5-9.
[21]	WANG X Y, CHANG S C. A 2D non-splitting unstructured triangular mesh Euler solver based on the space-time conservation element and solution element method[J]. Computational Fluid Dynamics Journal, 1999, 8(2):309-325.
[22]	王研艳, 翁春生. 尾喷管构型对多循环两相脉冲爆轰发动机流场及性能影响[J]. 航空动力学报, 2013, 28(10):2256-2266.
	WANG Y Y, WENG C S. Effects of nozzle on flow field and performance of multi-cycle two-phase pulse detonation engines[J]. Journal of Aerospace Power, 2013, 28(10):2256-2266. (in Chinese)
[23]	GORDON S, MCBRIDE B J. Computer program for calculation of complex chemical equilibrium compositions and applications Part 1:Analysis[R]. Cleveland,OH,US:NASA,Lewis Research Center, 1994.