高超声速进气道的裂解碳氢燃料提前喷注研究

推进技术 ›› 2018, Vol. 39 ›› Issue (1): 196-202.

高超声速进气道的裂解碳氢燃料提前喷注研究

朱呈祥,黄雨柔,陈荣钱,尤延铖

厦门大学航空航天学院，福建厦门 361005,厦门大学航空航天学院，福建厦门 361005,厦门大学航空航天学院，福建厦门 361005,厦门大学航空航天学院，福建厦门 361005

发布日期:2021-08-15
作者简介:朱呈祥，男，博士，讲师，研究领域为高超声速流动。E-mail: chengxiang.zhu@xmu.edu.cn 通讯作者:尤延铖，男，博士，教授，研究领域为高超声速推进系统设计。
基金资助:
自然科学基金(51606161；91441128；51276151)；国防基础科研(B1420133058)。

Pre-Injection of Cracked Hydrocarbon Fuel in Hypersonic Inlets

School of Aerospace Engineering，Xiamen University，Xiamen 361005，China,School of Aerospace Engineering，Xiamen University，Xiamen 361005，China,School of Aerospace Engineering，Xiamen University，Xiamen 361005，China and School of Aerospace Engineering，Xiamen University，Xiamen 361005，China

Published:2021-08-15

摘要/Abstract

摘要： 高超声速进气道的裂解碳氢燃料提前喷注一方面可以显著增加燃料的有效掺混长度，另一方面也可以实现对进气道激波和流场的控制。以替代裂解碳氢燃料C12H24为喷注气体，采用数值工具模拟高超声速二元进气道在飞行高度为26km时的工作状态，开展了马赫5设计状态无燃料喷注和马赫6超额定状态带燃料喷注的两类流场分析，重点研究燃料对波系的控制和燃料的自身掺混。通过调节五喷嘴的燃料喷注压力发现，按照马赫5设计的高超声速进气道在马赫6时同样可以实现完全激波贴口，燃料在进气道内通过多重外压缩激波作用也实现了与空气的完全掺混。同时，冷壁温条件下进气道内仅出现少量近壁燃烧，CO₂产物的质量百分比仅在10-7量级，进气道出口的总压恢复系数相较无化学反应时下降2.5%，但仍维持在0.5左右。还对比了五喷嘴、三喷嘴、五喷嘴后移和90°单喷嘴结构下进气道流场以及掺混效率的区别，结果表明，五喷嘴结构的进气道燃料喷注可以实现4倍喷注压力下的激波封口和快速完全掺混，而三喷嘴、后移五喷嘴和单喷嘴结构分别需要5倍、5倍、6.6倍来流静压实现进气道马赫6的激波贴口。

关键词: 高超声速进气道；裂解碳氢燃料；激波系控制；掺混效率

Abstract: Pre-injection of cracked hydrocarbon fuel in hypersonic inlets can increase the mixing length of the fuel significantly， and can also be utilized for inlet shock and flow control. In the present work， an alternative cracked fuel C12H24 is applied for the pre-injection. Numerical simulations were undertaken to investigate the performance of a two-dimensional hypersonic inlet designed at flight altitude 26km. The inlet flow feature at Mach 5 without fuel pre-injection， and at Mach 6 with fuel pre-injection were both analyzed. Emphasis was focused on the shock control effect and the fuel mixing efficiency. The results indicated that shock-on-lip at Mach 6 for the inlet (which was designed at Mach 5) can be obtained by adjusting the injection pressure. Fully-mixing of the fuel was also achieved through multiple-interaction of oblique shocks inside the inlet. With cooled surface， only small amount of pre-combustion was observed. The mass fraction of the generated CO₂ was only on the order of 10-7. The average total pressure recovery of the inlet decreased 2.5%， but still remained around 0.5. Compared to the flow field and the mixing efficiency of three parallel injectors， five downstream injectors and a single 90 degree injector， five parallel injectors can achieve shock-on-lip and fast fully-mixing with an injection pressure at 4 times the inflow pressure， whereas it was 5 times， 5 times， and 6.6 times of the inflow pressure for three parallel injectors， five downstream injectors and a single 90 degree injector， respectively.

Key words: Hypersonic inlet；Cracked hydrocarbon fuel；Shock control；Mixing efficiency

朱呈祥,黄雨柔,陈荣钱,尤延铖. 高超声速进气道的裂解碳氢燃料提前喷注研究[J]. 推进技术, 2018, 39(1): 196-202.

ZHU Cheng-xiang,HUANG Yu-rou,CHEN Rong-qian,YOU Yan-cheng. Pre-Injection of Cracked Hydrocarbon Fuel in Hypersonic Inlets[J]. Journal of Propulsion Technology, 2018, 39(1): 196-202.

参考文献

[1] Sislian J P, Parent B. Hypervelocity Fuel/Air Mixing in a Shcramjet Inlet[J]. Journal of Propulsion and Power, 2004, 20(2): 263-272.
[2] Parent B, Sislian J P. Schumacher J. Numerical Investigation of the Turbulent Mixing Performance of a Cantilevered Ramp Injector[J]. AIAA Journal, 2002, 40(8): 1559-1566.
[3] Parent B, Sislian J P. Hypersonic Mixing Enhancement by Compression at a High Convective Mach Number[J].AIAA Journal, 2004, 42(4): 787-795.
[4] Gardner A D, Paull A, McIntyre T J. Upstream Porthole Injection in a 2-D Scramjet Model[J]. Shock Waves, 2002, 11: 369-375.
[5] Kovachevich A L, Hajek K M, Mcintyre T J, et al. Imaging of Hydrogen Fuel Injection on the Intake of a Heated Wall Scramjet[R]. AIAA 2006-5039.
[6] Turner J C, Smart M K. Application of Inlet Injection to a Three-Dimensional Scramjet at Mach 8[J]. AIAA Journal, 2010, 48(4): 829-838.
[7] Fan X, Yu G, Li J, et al. Combustion and Ignition of Thermally Cracked Kerosene in Supersonic Model Combustors[J]. Journal of Propulsion and Power, 2007, 23(2): 317-324.
[8] Fan X, Yu G, Li J, et al. Investigation of Vaporized Kerosene Injection and Combustion in a Supersonic Model Combustor[J]. Journal of Propulsion and Power, 2006, 22(1): 103-110.
[9] 俞刚, 范学军. 超声速燃烧与高超声速推进[J]. 力学进展, 2013, 43(5): 449-471。
[10] Yu G, Li J G, Zhao J R, et al. An Experimental Study of Kerosene Combustion in a Supersonic Model Combustor Using Effervescent Atomization[J]. Proceedings of the Combustion Institute, 2005, 30: 2859-2866.
[11] 王曦, 仲峰泉, 陈立红, 等. 考虑煤油裂解效应的超声速燃烧室再生冷却过程分析 [J]. 推进技术, 2013, 34(1): 47-53. (WANG Xi, ZHONG Feng-quan, CHEN Li-hong, et al. A Coupled Heat Transfer Analysis with Effects of Catalytic Cracking of Kerosene for Actively Cooled Supersonic Combustor[J]. Journal of Propulsion Technology, 2013, 34(1): 47-53.)
[12] Haberle J, Gulhan A. Investigation of Two-Dimensional Scramjet Inlet Flowfield at Mach 7[J]. Journal of Propulsion and Power, 2008, 24(3): 446-459.
[13] Wang T S. Thermophysics Characterization of Kerosene Combustion[J]. Journal of Thermophysics and Heat Transfer, 2001, 15(2): 140-147.
[14] Tan H J, Li C H, Zhang Y. Investigation of a Fluidic Shock Control Method for Hypersonic Inlets[J]. Journal of Propulsion and Power, 2010, 26(5): 1072-1083.
[15] 谭慧俊, 陈智, 李光胜. 基于激波形状控制的定几何高超声速可调进气道概念与初步验证[J]. 中国科学(E辑):技术科学, 2007, 37(11): 1469-1479.
[16] Pudsey A S, Boyce R R. Numerical Investigation of Transverse Jets Through Multiport Injector Arrays in Supersonic Crossflow[J]. Journal of Propulsion and Power, 2010, 26(6): 1225-1236.
[17] 王枫, 张贵田, 黄日鑫. 入口非均匀流对亚燃燃烧室性能影响数值研究[J]. 航空工程进展, 2012, 3(2): 223-228.
[18] 徐榕, 李井华, 赵坚行, 等. 湍流燃烧模型对双旋流燃烧室喷雾燃烧的影响[J]. 推进技术, 2013, 34(3): 375-382. (XU Rong, LI Jing-hua, ZHAO Jian-xing, et al. Effects of Turbulent Combustion Models on Spray Combustion Flow of Dual-Stage Swirler Combustor [J]. Journal of Propulsion Technology, 34(3): 375-382.)(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2016-08-29；修订日期:2016-11-11。基金项目:自然科学基金(51606161；91441128；51276151)；国防基础科研(B1420133058)。作者简介:朱呈祥,男,博士,讲师,研究领域为高超声速流动。E-mail: chengxiang.zhu@xmu.edu.cn通讯作者:尤延铖,男,博士,教授,研究领域为高超声速推进系统设计。E-mail: yancheng.you@xmu.edu.cn