碳氢燃料超燃冲压发动机热非平衡效应

doi:10.7527/S1000-6893.2023.29399

Abstract

Abstract:

Hypersonic flow is generally accompanied by the thermochemical non-equilibrium effect， which brings a series of effects on the flow and combustion in hypersonic propulsion systems. This paper gives a numerical investigation of the effects of thermal nonequilibrium on flow， combustion and engine performance by simulating the kerosene-fueled scramjet at the free-stream conditions of Mach number 10 and 29 km. The thermochemical nonequilibrium and thermal equilibrium models are employed in this study. The results show that the thermal non-equilibrium effect can change the flow field structure and mixing efficiency in the engine by increasing the angle of oblique shock wave. The equilibrium temperature at the front of the combustion chamber is higher in the thermal non-equilibrium state， which can promote the combustion upstream of the cavity. However， the effect of thermal non-equilibrium reduces the peak heat release rate and combustion efficiency downstream of the cavity. The vibrational non-equilibrium in the nozzle can affect the thrust. In general， thermal non-equilibrium effects can reduce the performance of kerosene-fueled scramjet at Mach number 10.

Key words: hypersonic flow, thermochemical nonequilibrium, two-temperature model, scramjet, hydrocarbon fuel

CLC Number:

V430

You WU, Bing CHEN, Qingchun YANG, Xu XU. Effects of thermal nonequilibrium on hydrocarbon⁃fueled scramjets[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529399-529399.

Figures/Tables 22

Table 1

Fig.1

Fig.2

Fig.3

Fig.4

Table 2

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

Fig.18

Table 3

Fig.19

References 34

1	URZAY J. Supersonic combustion in air-breathing propulsion systems for hypersonic flight［J］. Annual Review of Fluid Mechanics， 2018， 50： 593-627.
2	岳连捷，张旭，张启帆，等. 高马赫数超燃冲压发动机技术研究进展［J］. 力学学报， 2022， 54（2）： 263-288.
	YUE L J， ZHANG X， ZHANG Q F， et al. Research progress on high-Mach-number scramjet engine technologies［J］. Chinese Journal of Theoretical and Applied Mechanics， 2022， 54（2）： 263-288 （in Chinese）.
3	GIORDANO D. Impact of the Born-Oppenheimer approximation on aerothermodynamics［J］. Journal of Thermophysics and Heat Transfer， 2007， 21（3）： 647-657.
4	李海燕. 高超声速高温气体流场的数值模拟［D］. 绵阳：中国空气动力研究与发展中心， 2007： 20-22.
	LI H Y. Numerical simulation of hypersonic and high temperature gas flowfields［D］.Mianyang： China Aerodynamics Research and Development Center， 2007： 20-22 （in Chinese）.
5	NAGNIBEDA E， KUSTOVA E. Non-equilibrium reacting gas flows： Kinetic theory of transport and relaxation processes［M］. Berlin， Heidelberg： Springer， 2009.
6	SCHMISSEUR J D. Hypersonics into the 21st century： A perspective on AFOSR-sponsored research in aerothermodynamics［J］. Progress in Aerospace Sciences， 2015， 72： 3-16.
7	FIÉVET R， RAMAN V. Effect of vibrational nonequilibrium on isolator shock structure［J］. Journal of Propulsion and Power， 2018， 34（5）： 1334-1344.
8	DAI C L， SUN B， ZHOU C S， et al. Numerical investigation of real-gas effect of inward-turning inlet at Mach 12［J］. Aerospace Science and Technology， 2021， 115： 106786.
9	韩亦宇，张若凌，邢建文，等. 热力学非平衡对超燃冲压发动机冷态流动影响研究［J］. 推进技术， 2022， 43（7）： 210262.
	HAN Y Y， ZHANG R L， XING J W， et al. Effects of thermal nonequilibrium on cold flow in scramjets［J］. Journal of Propulsion Technology， 2022， 43（7）： 210262 （in Chinese）.
10	KOO H， RAMAN V， VARGHESE P L. Direct numerical simulation of supersonic combustion with thermal nonequilibrium［J］. Proceedings of the Combustion Institute， 2015， 35（2）： 2145-2153.
11	FIÉVET R， VOELKEL S， KOO H， et al. Effect of thermal nonequilibrium on ignition in scramjet combustors［J］. Proceedings of the Combustion Institute， 2017， 36（2）： 2901-2910.
12	AO Y， WU K， LU H B， et al. Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions［J］. Acta Astronautica， 2023， 208： 281-295.
13	YAO W. Nonequilibrium effects in hypersonic combustion modeling［J］. Journal of Propulsion and Power， 2022， 38（4）： 523-540.
14	YAO W， LIU H， ZHANG Z， et al. Effects of thermal/chemical nonequilibrium on a high-Mach ethylene-fueled scramjet［J］. Journal of Propulsion and Power， 2023， 39（4）： 562-579.
15	ZIDANE A， HAOUI R， SELLAM M， et al. Numerical study of a nonequilibrium H₂—O₂ rocket nozzle flow［J］. International Journal of Hydrogen Energy， 2019， 44（8）： 4361-4373.
16	LEE J H. Basic governing equations for the flight regimes of aeroassisted orbital transfer vehicles［C］∥ 19th Thermophysics Conference. Reston： AIAA， 1984： 1729.
17	SKREBKOV O V. Vibrational non-equilibrium in the hydrogen-oxygen reaction. Comparison with experiment［J］. Combustion Theory and Modelling， 2015， 19（2）： 131-158.
18	MILLIKAN R C， WHITE D R. Systematics of vibrational relaxation［J］. The Journal of Chemical Physics， 1963， 39（12）： 3209-3213.
19	HALL J G. Fundamental phenomena in hypersonic flow［M］. Ithaca： Cornell University Press， 1966.
20	CANDLER G. Computation of thermo-chemical nonequilibrium Martian atmospheric entry flows［C］∥ 5th Joint Thermophysics and Heat Transfer Conference. Reston： AIAA， 1990： 1695.
21	MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications［J］. AIAA Journal， 1994， 32（8）： 1598-1605.
22	WESTBROOK C K， DRYER F L. Simplified reaction mechanisms for the oxidation of hydrocarbon fuels in flames［J］. Combustion Science and Technology， 1981， 27（1-2）： 31-43.
23	KNAB O， FRUEHAUF H H， MESSERSCHMID E W. Theory and validation of the physically consistent coupled vibration-chemistry-vibration model［J］. Journal of Thermophysics and Heat Transfer， 1995， 9（2）： 219-226.
24	VOELKEL S， RAMAN V， VARGHESE P L. Effect of thermal nonequilibrium on reactions in hydrogen combustion［J］. Shock Waves， 2016， 26（5）： 539-549.
25	WU Y， XU X， CHEN B， et al. Theoretical and numerical study of the binary scaling law for electron distribution in thermochemical non-equilibrium flows under extremely high Mach number［J］. Journal of Fluid Mechanics， 2022， 940： A3.
26	吴忧，徐旭，陈兵，等. 高马赫数下横/逆向喷流干扰流场数值研究［J］. 航空学报， 2021， 42（S1）： 726359.
	WU Y， XU X， CHEN B， et al. Numerical study on transverse/opposing jet interaction flowfield under high Mach number［J］. Acta Aeronautica et Astronautica Sinica， 2021， 42（S1）： 726359 （in Chinese）.
27	KIM S D， LEE B J， LEE H J， et al. Robust HLLC riemann solver with weighted average flux scheme for strong shock［J］. Journal of Computational Physics， 2009， 228（20）： 7634-7642.
28	PARK J S， YOON S H， KIM C. Multi-dimensional limiting process for hyperbolic conservation laws on unstructured grids［J］. Journal of Computational Physics， 2010， 229（3）： 788-812.
29	VENKATAKRISHNAN V. On the accuracy of limiters and convergence to steady state solutions［C］∥31st Aerospace Sciences Meeting. Reston： AIAA， 1993： 880.
30	BLAZEK J. Computational fluid dynamics： Principles and applications［M］. 3rd ed. Oxford： Butterworth Heinemann， 2015.
31	LEHR H F.Experiments on shock-induced combustion［J］.Astronautica Acta， 1972， 17（4）：589-597.
32	DU P， XUE R， WU Y K， et al. Study on the flow field of a kerosene-fueled integrated inlet-combustor-nozzle oblique detonation engine［J］. Physics of Fluids， 2023， 35（6）： 066127.
33	WANG Y Y， CHENG K L， TANG J F， et al. Analysis of the maximum flight Mach number of hydrocarbon-fueled scramjet engines under the flight cruising constraint and the combustor cooling requirement［J］. Aerospace Science and Technology， 2020， 98： 105594.
34	KUMARAN K， BEHERA P R， BABU V. Numerical investigation of the supersonic combustion of kerosene in a strut-based combustor［J］. Journal of Propulsion and Power， 2010， 26（5）： 1084-1091.

化学反应	全部T_v		0.5T≤T_v≤1.2T
化学反应	ξ	Error	ξ	Error
H+O₂（T_v）	0.307	0.058	0.162	0.012
O+H₂（T_v）	0.155	0.064	0.071	0.010
OH+H₂（T_v）	0.114	0.020	0.087	0.016
OH（T_v）+H₂	0.016	0.004	0.012	0.003

参数	EQ	NEQ
捕获流量/（kg·s^-1）	0.924	0.916
压力对推力的贡献/N	566.0	548.8
摩擦阻力/N	346.8	342.8
净推力/N	219.2	206.0
比冲/s	398.5	374.5

[1]	Hongwei QIAO, Jianhan LIANG, Lin ZHANG, Mingbo SUN, Yuqiao CHEN. Research progress of probability density function approach in supersonic combustion [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 28802-028802.
[2]	Xiaoyong LIU, Mingfu WANG, Jianwen LIU, Xin REN, Xuan ZHANG. Review and prospect of research on scramjet [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529878-529878.
[3]	Bing WAN, Jun CHEN, Hanchen BAI. Full flow path performance design method for wide range scramjet based on equivalent thermodynamic process [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(4): 128757-128757.
[4]	Jianheng JI, Zun CAI, Taiyu WANG, Mingbo SUN, Zhenguo WANG. Flow and combustion process for wide speed range scramjet: Review [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(3): 28696-028696.
[5]	Tao TANG, Jiangfei YU, Yuhui HUANG, Hongbo WANG, Mingbo SUN, Guoyan ZHAO, Dapeng XIONG, Zhenguo WANG. Analysis of structure and regime of ethylene fuel injection flame in circular⁃section supersonic combustor [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 528880-528880.
[6]	Dingyuan WEI, Silong ZHANG, Jianfei WEI, Jingying ZUO, Xin LI, Wen BAO. Thermal protection and drag reduction characteristics of discrete hole film cooling in high Mach number combustor [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529075-529075.
[7]	Xiang ZHAO, Zhixun XIA, Chuanbo FANG, Likun MA, Chaolong LI, Yifan DUAN. Theoretical analysis of performance of solid rocket scramjet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(5): 126971-126971.
[8]	Yushu JIN, Xu XU, Qingchun YANG. Research progress in combustion characteristics and engine applications of energetic hydrocarbon fuels [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(5): 26690-026690.
[9]	Chongli MA, Jingyuan LIU. Effect of grid strategy on numerical simulation results of aerothermal heating loads over hypersonic blunt bodies [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(5): 126710-126710.
[10]	Jiahui SONG, Aiguo XU, Long MIAO, Yugan LIAO, Fuwen LIANG, Feng TIAN, Mingqing NIE, Ningfei WANG. Entropy increase characteristics of shock wave/plate laminar boundary layer interaction [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 528520-528520.
[11]	Zhixun XIA, Yunchao FENG, Likun MA, Binbin CHEN, Chaolong LI, Pengnian YANG, Yandong LIU, Ying QU, Kangchun ZHAO, Libei ZHAO, Penghao REN. Research progress of solid rocket scramjet combustion technology [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528793-528793.
[12]	Bo DING, Zhenli CHEN, Zihan JIAO, Jincheng WANG, Zheng LI, Guanghui BAI. Unsteady control mechanisms of hypersonic compression corner using pulsed surface arc discharge [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127744-127744.
[13]	Yifeng HUANG, Shuhua ZENG, Zhongzheng JIANG, Weifang CHEN. Numerical study on high-altitude lateral jet based on nonlinear coupled constitutive relation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 8-22.
[14]	LI Chaolong, XIA Zhixun, MA Likun, ZHAO Xiang, LUO Zhenbing, DUAN Yifan. Experiment on performance of solid rocket scramjet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 126075-126075.
[15]	LIU Pengxin, YUAN Xianxu, SUN Dong, FU Yalu, LI Chen. Direct numerical simulation of high-temperature turbulent boundary layer with chemical nonequilibrium [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124877-124877.

Effects of thermal nonequilibrium on hydrocarbon⁃fueled scramjets

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 22

References 34

Related Articles 15

Recommended Articles

Metrics

Comments