两次进气对固体火箭冲压组合发动机燃烧和烧蚀环境的影响

doi:10.12382/bgxb.2021.0200

摘要/Abstract

摘要： 为给固体火箭冲压组合发动机补燃室的进气道设计提供参考，研究了空气两次进气对补燃室燃烧效率和内壁烧蚀环境的影响。采用标准k-ε(k为湍流动能，ε为耗散率)模型、涡耗散模型和King硼颗粒点火模型，分别对空气一次进气和两次进气两种补燃室的多相流燃烧进行数值模拟，并进行对比分析。研究结果表明：两次进气可包覆混合燃气，并将其向内挤压，压缩高温区域，改变氧气分布，从而减小高温内壁面积，降低低温壁面温度，减少贴近壁面的凝聚相颗粒数量，从而减弱对壁面的热烧蚀、氧化和凝聚相颗粒侵蚀作用，同时，因造成的动能损失更大，减小了贴近内壁的气流速度，可减弱气流冲刷作用，二者共同作用，较大程度改善补燃室内壁的烧蚀环境；两次进气对补燃室的燃烧效率影响不大，一次进气和两次进气补燃室的总燃烧效率分别为80.68%和80.18%；综合燃烧效率和内壁烧蚀环境两方面，表明两次进气形式优于一次进气形式。

关键词: 固体火箭冲压组合发动机, 补燃室, 两次进气, 燃烧效率, 内壁烧蚀环境

Abstract: The effect of twice air-entering on the combustion efficiency of afterburner and the ablation environment of inner wall was studied for the design of air-inlet of solid rocket ramjet afterburner. The standard k-ε model, the eddy dissipation model and the King boron particle ignition model were adopted to simulate the multiphase combustion in the single and twice air-entering afterburners. Through comparative analysis，the following conclusions were drawn as follow. The twice air-entering can coat the mixed gas and squeeze it inward to compress the high temperature area and changeg the oxygen distribution，which reduces the area of the high temperature inner wall，decrease the temperature of the low temperature wall，and cut down the number of condensed phase particles close to the wall，thereby weakening the thermal ablation，oxidation and erosion of condensed particles in the inner wall.Because of the greater kinetic energy loss which reduces the airflow velocity close to the inner wall，it also weakens the airflow scouring effect.Thus the ablation environment in the inner wall of afterburner is improved. However，twice air-entering has little effect on the combustion efficiency，and the total combustion efficiencies of afterburners with single air-entering and twice air-entering reach 80.68% and 80.18%, respectively. Considering the two aspects of combustion efficiency and ablation environment of the inner wall, it can be considered that twice air-entering is better than once air-entering.

Key words: solidrocketramjet, afterburner, twiceair-entering, combustionefficiency, ablationenvironmentofinnerwall

中图分类号:

V438

温怡豪，王金金，查柏林，徐志高. 两次进气对固体火箭冲压组合发动机燃烧和烧蚀环境的影响[J]. 兵工学报, 2022, 43(4): 804-813.

WEN Yihao, WANG Jinjin, ZHA Bailin, XU Zhigao. Influence of Twice Air-entering on the Combustion and Ablation Environment of Solid Rocket Ramjet[J]. Acta Armamentarii, 2022, 43(4): 804-813.

参考文献

［1］鲍福廷，黄熙军，张振鹏,等.固体火箭冲压组合发动机［M］.北京:中国宇航出版社，2006: 1-2.
BAO F T，HUANG X J，ZHANG Z P，et al. Integral solid propellant ramjet rocket motor［M］.Beijing: China Aerospace Publishing House，2006:1-2. (in Chinese)
［2］ PEIN R，VINNEMEIER F. Swirl and fuel composition effects on boron combustion in solid-fuel ramjets［J］. Journal of Propulsion and Power，1992，3(8):609-614.
［3］ VIGOT C，COCHET A，GUIN C.Combustion behavior of boron-based solid propellants in a ducted rocket［J］. International Journal of Energetic Materials & Chemical Propulsion，1991，2(1/2/3/4/5/6):386-401.
［4］胡春波，李强，何洪庆，等.喷口数与进气道角对固冲发动机补燃室气流掺混的影响［J］.固体火箭技术，2003,26(4):14-17.
HU C B，LI Q，HE H Q，et al. Effects of the air inlet angle and jet number on mixing flow in the afterburning chamber of solid rocket ramjet［J］.Journal of Solid Rocket Technology，2003,26(4):14-17. (in Chinese)
［5］许超.补燃室结构对冲压发动机二次燃烧影响研究［D］. 西安:西北工业大学，2007.
XU C.Influence of after-burning chamber configuration on the secondary combustion of ramjet［D］.Xi'an: Northwestern Polytechnical University，2007. (in Chinese)
［6］李敏剑，严聪，冯锦虎，等.进气道直径大小对固冲发动机内流场的影响研究［J］.弹箭与制导学报，2010，30(1):153-156.
LI M J，YAN C，FENG J H，et al.Researches on different diameters of air-inlet pipe's influences to the inside flow field of a solid rocket ramjet engine［J］.Journal of Projectiles，Rockets，Missiles and Guidance，2010，30(1):153-156. (in Chinese)
［7］赵洪章，李进贤，曹琪.进气形式对冲压发动机二次燃烧的影响［J］.弹箭与制导学报，2011，31(2):114-116.
ZHAO H Z，LI J X，CAO Q. The effect of inlet mode on after-burning of ramjet［J］.Journal of Projectiles， Rockets，Missiles and Guidance，2011， 31(2):114-116. (in Chinese)
［8］李洁，冯喜平，李进贤，等.二次进气角度对固冲发动机掺混燃烧的影响［J］.科学技术与工程，2013，13(16):4757-4760.
LI J，FENG X P，LI J X，et al. Influence of secondary air-in angle on the SDR mixing combustion［J］. Science Technology and Engineering，2013，13(16):4757-4760. (in Chinese)
［9］王洪远，徐义华，胡旭，等.空气旋转进气对含硼固体冲压发动机二次燃烧性能影响的研究［J］.兵工学报，2015，36(4): 619-625.
WANG H Y，XU Y H，HU X，et al. Research on the characteristics of secondary combustion of boron-based ducted rocket with swirling air injection［J］.Acta Armamentarii，2015，36(4):619-625. (in Chinese)
［10］ XU Y H，JIA R，MEDINA H，et al. Effect of tangential swirl air inlet angle on the combustion efficiency of a hybrid powder-solid ramjet［J］.Acta Astronautica，2019，159:87-95.
［11］ LI W X，CHEN X，SU Y L，et al.Combustion characteristics of paraffin-polyethylene blends fuel for solid fuel ramjet［J］. Journal of Aerospace Engineering，2020， 33(4):78-90.
［12］崔立堃，杜明明，叶伟.固冲发动机补燃室化学非平衡流数值模拟［J］.兵器装备工程学报，2021，42(1):157-160， 173.
CUI L K，DU M M，YE W. Numerical simulation for chemical non-equilibrium flow in combustion chamber of SDR［J］. Journal of Ordnance Equipment Engineering， 2021， 42(1): 157-160，173. (in Chinese)
［13］ KING M K. Boron ignition and combustion in air-augmented rocket afterburner［J］. Combustion Science and Technology， 1972，5(1):155-164.
［14］ KING M K. Boron particle ignition in hot gas streams［J］. Combustion Science and Technology，1974，8(5/6):255-273.
［15］ KING M K. Ignition and combustion of boron particles and clouds［J］. Journal of Spacecraft，1982，19(4):294-306.
［16］胡建新.含硼推进剂固体火箭冲压发动机补燃室工作过程研究［D］.长沙:国防科学技术大学，2006.
HU J X.Research on the secondary combustion chamber operation process of boron-based propellant ducted rockets［D］.Changsha:National University of Defense Technology，2006. (in Chinese)
［17］周俊虎，刘建忠，张彦威，等. 硼的点火和燃烧［M］. 北京: 科学出版社，2015: 9-11.
ZHOU J H，LIU J Z，ZHANG Y W，et al. Ignition and combustion of boron［M］. Beijing: Science Press，2015: 9-11. (in Chinese)
［18］ HASHIM S A，KARMAKAR S，ROY A.Combustion characteristics of boron-HTPB-based solid fuels for hybrid gas generator in ducted rocket applications［J］.Combustion Science and Technology，2019，191(11):2082-2100.
［19］方传波.固体火箭冲压发动机内硼颗粒着火燃烧过程研究［D］.长沙:国防科学技术大学，2014.
FANG C B. Study of ignition and combustion process of boron particles in ducted rockets［D］.Changsha:National University of Defense Technology，2014. (in Chinese)
［20］ KURTH G，BAUER C，MEYER T，et al. Development and testing of a C/SiC combustion chamber for high speed throttleable ducted rocket applications［C］∥Proceedings of the 51st AIAA/SAE/ASEE Joint Propulsion Conference. Orlando，FL, US：AIAA，2015.
［21］田凌寒，张强，李逢舟.碳化硅陶瓷基复合材料在固冲发动机上的应用［J］弹箭与制导学报，2020，40(5):72-75.
TIAN L H，ZHANG Q，LI F Z. Application of silicon carbide based composite in solid propellant ramjet［J］. Journal of Projectiles，Rockets，Missiles and Guidance，2020，40(5):72-75. (in Chinese)
［22］查柏林，石易昂，王金金，等. 固体火箭冲压发动机补燃室绝热层烧蚀试验方法［J］.航空动力学报，2018， 33(4):936-943.
ZHA B L，SHI Y A，WANG J J，et al. Ablation experimental method for insulation of secondary combustion chamber in solid ducted rocket［J］. Journal of Aerospace Power，2018，33(4):936-943. (in Chinese)

[1]	纪明，卜珺珺，马聪. 最大熵试验法对航天作动器输出可靠性的评估[J]. 兵工学报, 2022, 43(4): 919-923.
[2]	杨亚军，王召巴. 固体火箭发动机衬层固化状态超声波实时监测方法[J]. 兵工学报, 2014, 35(5): 697-702.