The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine

doi:10.12382/bgxb.2024.0171

Abstract

Abstract:

The influences of forebody compression methods and compression levels on the thrust performance of oblique detonation engine (ODE) are studied.The effects of 1-,2-,and 3-stage oblique shocks and compression angles on the thrust performance of hydrogen-air ODE under flight conditions of Mach number 10 and altitude 35km are examined through theoretical analysis.The results indicate a significant enhancement in thrust performance with an increase in the number of compression stages.Within the range of compression angles from 2° to 24°,the fuel specific impulse exhibits an initial increase followed by a decrease with the increase in the compression angle of the 1st stage,while the increases in the angles of the 2nd and 3rd compression lead to a continuous improvement in fuel specific impulse,thus delaying the appearance of peak thrust performance.Analysis of the impact of inlet compression stages on the total pressure at the outlet of inlet duct,the exit of mixing section,and the exit of combustion chamber reveals that the increase in the compression angle of the 1st stage wedge leads to a rapid rise in the outlet airflow temperature of inlet duct,limiting the pressure-gain capability of detonation combustion.Conversely,the multi-stage compression achieves higher combustion product pressure and velocity,thereby enhancing the thrust performance and reducing the total pressure loss.

Key words: oblique detonation engine, forebody compression, combustion pressure, combustion velocity, specific impulse

XI Xuechen, WANG Anqi, NIU Shuzhen, YANG Pengfei. The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine[J]. Acta Armamentarii, 2025, 46(8): 240171-.

Figures/Tables 9

Fig.1 Schematics of oblique detonation engine and inlet compression methods

Fig.2 Fuel specific impulse and thrust with different inlet compression angles

Fig.3 The total pressure of airflows at inlet exit,mixing section exit and the combustor exit under different levels of inlet compression

Fig.4 Gas pressure and velocity at combustor exit for different inlet compression stages

Fig.5 Nozzle exit velocity and pressure with different expansion area ratios

Fig.6 Total pressure of inlet-compressed gas and detonation product with different inlet compression angles

Fig.7 Temperature and velocity of inlet-compressed gas-stream with different inlet compression angles

Fig.8 Pressures and velocities of detonation products at different inlet compression angles

Fig.9 Nozzle exit velocity at different inlet compression angles

References 25

[1]	LEE J H S. The detonation phenomenon[M]. Cambridge,MA,US: Cambridge University Press, 2008.
[2]	PRIGENT A, PITON D, SERRE L, et al. Performance of a valveless air breathing pulse detonation engine[C]// Proceedings of the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Fort Lauderdale,FL,US: AIAA, 2004:3749.
[3]	ANAND V, GUTMARK E. Rotating detonation combustors and their similarities to rocket instabilities[J]. Progress in Energy and Combustion Science, 2019, 73:182-234.
[4]	滕宏辉, 姜宗林. 斜爆轰的多波结构及其稳定性研究进展[J]. 力学进展, 2020, 50:202002.
	TENG H H, JIANG Z L. Progress in multi-wave structure and stability of oblique detonations[J]. Advances in Mechanics, 2020, 50:202002. (in Chinese)
[5]	滕宏辉, 杨鹏飞, 张义宁, 等. 斜爆轰发动机的流动与燃烧机理[J]. 中国科学:物理学力学天文学, 2020, 50:090008.
	TENG H H, YANG P F, ZHANG Y N, et al. Flow and combustion mechanism of oblique detonation engines[J]. Science China:Physics,Mechanics & Astronomy, 2020, 50:090008. (in Chinese)
[6]	JIANG Z L, ZHANG Z J, LIU Y, et al. Criteria for hypersonic airbreathing propulsion and its experimental verification[J]. Chinese Journal of Aeronautics, 2021, 34:94-104.
[7]	QIN Q Y, ZHANG X B. A novel method for trigger location control of the oblique detonation wave by a modified wedge[J]. Combustion and Flame, 2018, 197:65-77.
[8]	ZHANG G Q, GAO S F, XIANG G X. Study on initiation mode of oblique detonation induced by a finite wedge[J]. Physics of Fluids, 2021, 33(1):016102.
[9]	TENG H H, JIANG Z L, NG H D. Numerical study on unstable surfaces of oblique detonations[J]. Journal of Fluid Mechanics, 2014, 744:111-128.
[10]	TENG H H, TIAN C, ZHANG Y N, et al. Morphology of oblique detonation waves in a stoichiometric hydrogen-air mixture[J]. Journal of Fluid Mechanics, 2021, 913:A1.
[11]	边靖, 周林, 滕宏辉. 两种前体压缩方式对斜爆震燃烧影响的数值研究[J]. 推进技术, 2021, 42(4):816-826.
	BIAN J, ZHOU L, TENG H H. Numerical study on ef-fects of two forebody compression methods on oblique detonation combustion[J]. Journal of Propulsion Technology, 2021, 42(4):816-826. (in Chinese)
[12]	YANG P F, NG H D, TENG H H. Unsteady dynamics of wedge-induced oblique detonations under periodic inflows[J]. Physics of Fluids, 2021, 33:016107.
[13]	YANG P F, TENG H H, NG H D, et al. A numerical study on the instability of oblique detonation waves with a two-step induction-reaction kinetic model[J]. Proceedings of the Combustion Institute, 2019, 37:3537-3544.
[14]	WANG K L, YANG P F, TENG H H. Steadiness of wave complex induced by oblique detonation wave reflection before an expansion corner[J]. Aerospace Science and Technology, 2021, 112:106592.
[15]	WANG K L, ZHANG Z J, YANG P F, et al. Numerical study on reflection of an oblique detonation wave on an outward turning wall[J]. Physics of Fluids, 2020, 32:046101.
[16]	VALORANI M, DI GIACINTO M, BUONGIORNO C. Performance prediction for oblique detonation wave engines (odwe)[J]. Acta Astronautica, 2001, 48:211-228.
[17]	张子健. 斜爆轰推进理论、技术及其实验验证[D]. 北京: 中国科学院大学, 2020:72-83.
	ZHANG Z J. Oblique detonation propulsion theory,technology and its experimental demonstration[D]. Beijing: University of Chinese Academy of Sciences, 2020:72-83. (in Chinese)
[18]	马凯夫, 张子健, 刘云峰, 等. 斜爆轰发动机流动机理分析[J]. 气体物理, 2019, 4(3):1-10.
	MA K F, ZHANG Z J, LIU Y F, et al. Flow mechanism of oblique detonation engines[J]. Physics of Gases, 2019, 4(3):1-10. (in Chinese)
[19]	陈嘉豪, 张义宁, 杨晖, 等. 斜爆震发动机进气道与燃烧室一体化设计仿真研究[J]. 推进技术, 2018, 39(9):1938-1947.
	CHEN J H, ZHANG Y N, YANG H, et al. Numerical simulation on integrated design inlet and combustion chamber of oblique detonation engine[J]. Journal of Propulsion Technology, 2018, 39(9):1938-1947. (in Chinese)
[20]	杨鹏飞, 张子健, 杨瑞鑫, 等. 斜爆轰发动机的推力性能理论分析[J]. 力学学报, 2021, 53(10):2853-2864.
	YANG P F, ZHANG Z J, YANG R X, et al. Theorical study on propulsive performance of oblique detonation en-gine[J]. Chinese Journal of Theoretical and Applied Mechanics, 2021, 53(10):2853-2864. (in Chinese)
[21]	黄恩, 史爱明. 斜爆轰波总压规律及其在爆轰发动机分析模型中的应用[J]. 力学学报, 2023, 55(9):1892-1899.
	HUANG E, SHI A M. The law of total pressure of oblique detonation wave and its application in detonation engine analysis model[J]. Chinese Journal of Theoretical and Applied Mechanics, 2023, 55(9):1892-1899. (in Chinese)
[22]	代春良, 孙波, 卓长飞, 等. 前缘钝化和化学非平衡效应对斜爆震发动机进气道特性的影响[J]. 推进技术, 2022, 43(1):200751.
	DAI C L, SUN B, ZHUO C F, et al. Influence of leading edge blunt and chemical non-equilibrium effect on characteristics of inlet of oblique detonation engine[J]. Journal of Propulsion Technology, 2022, 43(1):200751. (in Chinese)
[23]	BURKE M P, CHAOS M, JU Y, et al. Comprehensive H₂/O₂ kinetic model for high-pressure combustion[J]. International Journal of Chemical Kinetics, 2012, 44:444-474.
[24]	童秉纲, 孔祥言, 邓国华. 气体动力学[M]. 北京: 高等教育出版社, 2012.
	TONG B G, KONG X Y, DENG G H. Gas-dynamics[M]. Beijing: Higher Education Press, 2012. (in Chinese)
[25]	MCBRIDE B J, ZEHE M J, GORDON S. NASA Glenn coefficients for calculating thermodynamic properties of individual species,Report No.2002-211556[R]. Cleveland,OH,US: National Aeronautics and Space Administration, 2002.