Study on spray and combustion characteristics of LOX/LCH4 pintle injector
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摘要:
为对液氧/液甲烷（LOX/LCH4）针栓式喷注器的优化设计提供指导，设计了具有矩形燃烧室的氧化剂中心式液氧/液甲烷针栓式喷注器，通过数值模拟探究其在不同喷注压降条件下的喷雾燃烧特性。结果表明：当保证各路推进剂质量流量不变时，增加径向液氧喷注压降会减小阻塞因子，不利于轴向液甲烷的快速雾化，会促进燃烧高温向喷管扩散，导致较低的燃烧效率；增加轴向液甲烷喷注压降会减小总动量比，不利于燃烧室头部贫氧流场的形成，容易促进燃烧室头部局部燃烧高温的发展；两路推进剂压降的最佳取值均为室压的22%。针栓式喷注器两股推进剂的撞击方式有利于化学能量的快速扩散，形成稳定的涡结构与剪切式火焰，能够保证良好的燃烧稳定性。
Abstract:To guide the optimization design of a liquid oxygen/liquid methane (LOX/LCH4) pintle injector, an oxidant-centered LOX/LCH4 pintle injector with a rectangular combustion chamber was processed, and its spray and combustion characteristics were explored through numerical simulation under different pressure drop conditions. Results showed that when the mass flow rate of each propellant was kept constant, increasing the pressure drop of radial LOX could decrease the block factor, which was not conducive to the rapid atomization of the axial LCH4, contributing to the development of the high combustion temperature towards the nozzle, and leading to lower combustion efficiency. Increasing the pressure drop of the axial LCH4 could decrease the total momentum ratio, which was not helpful for the formation of the poor-oxygen region on the head of the combustion chamber, resulting in the development of a local high combustion temperature. The optimal value of the pressure drop of both propellants was 22% of the combustion chamber pressure. The impact way of the two propellants of the pintle injector was beneficial to the rapid diffusion of chemical energy and can form stable vortices and shear layer flame, thus ensuring good combustion stability.
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图 2 液氧轨迹与氧气质量分数分布的试验结果与数值模拟结果的对比
Figure 2. Comparison of experimental results with numerical simulation results on tracks of LOX and distribution of oxygen mass fraction
图 5 不同网格分辨率下针栓头部沿燃烧室展向中心线的甲烷气质量分数分布
Figure 5. Methane mass fraction distribution on central line of pintle head along chamber width in different mesh resolution conditions
图 6 基准工况燃烧室头部中心截面甲烷、氧气、氮气质量分数分布云图，温度分布云图，流线分布与离散相轨迹
Figure 6. Mass fraction contour of methane, oxygen and nitrogen, temperature contour, streamline distribution and tracks of discrete phase on central plane of head of combustion chamber in fundamental case
图 7 不同液氧喷注压降条件下液甲烷SMD沿燃烧室轴向分布
Figure 7. SMD distribution of LCH4 along axial direction of chamber in different LOX injection pressure drop conditions
图 8 不同液氧喷注压降条件下燃烧室中心截面甲烷、氧气质量分数分布云图，混合时间尺度分布云图和温度分布云图
Figure 8. Mass fraction contour of methane and oxygen, mixing time scale contour and temperature contour on central plane of combustion chamber in different LOX injection pressure drop conditions
图 9 不同液甲烷喷注压降条件下液甲烷SMD沿燃烧室轴向分布
Figure 9. SMD distribution of LCH4 along axial direction of chamber in different LCH4 injection pressure drop conditions
图 10 不同液甲烷喷注压降条件下燃烧室中心截面甲烷、氧气质量分数分布云图，混合时间尺度分布云图与温度分布云图
Figure 10. Mass fraction contour of methane and oxygen, mixing time scale contour and temperature contour on central plane of combustion chamber in different LCH4 injection pressure drop conditions
表 1 不同喷注压降条件下液氧/液甲烷针栓式喷注器喷雾燃烧定常数值模拟工况
Table 1. Steady numerical simulation cases of spray and combustion in a LOX/LCH4 pintle injector in different injection pressure drop conditions
工况 轴向液甲烷 径向液氧 总动量比 阻塞因子 燃烧效率/% 速度/（m/s） 压降/MPa 环缝宽度/mm 速度/（m/s） 压降/MPa 孔径/mm C-A# 49.1 0.8 0.165 30.0 0.8 25×φ 0.60 0.9 0.30 97.98 CG-E1# 49.1 0.8 0.165 21.2 0.4 25×φ 0.72 0.6 0.36 99.50 CG-E2# 49.1 0.8 0.165 36.7 1.2 25×φ 0.55 1.1 0.27 98.73 CG-E3# 34.8 0.4 0.232 30.0 0.8 25×φ 0.60 1.2 0.30 99.25 CG-E4# 60.2 1.2 0.135 30.0 0.8 25×φ 0.60 0.7 0.30 98.77 
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[1] CASIANO M J, HULKA J R, YANG V. Liquid-propellant rocket engine throttling: a comprehensive review[J]. Journal of Propulsion and Power, 2010, 26(5): 897-923. doi: 10.2514/1.49791 [2] ZHOU Rui, SHEN Chibing. Influence of momentum ratio control mode on spray and combustion characteristics of a LOX/LCH4 pintle injector[J]. Journal of Zhejiang University: Science A, 2022, 23(5): 415-420. doi: 10.1631/jzus.A2100402 [3] ZHOU Rui, SHEN Chibing. Experimental study on the spray characteristics of a pintle injector element[J]. Acta Astronautica, 2022, 194: 255-262. doi: 10.1016/j.actaastro.2022.02.019 [4] GORDON D. Summary of deep throttling rocket engines with emphasis on Apollo LMDE[R]. AIAA2006-5220, 2006. [5] YU Nanjia, ZHOU Chuang, CAI Guobiao, et al. 2.5 kN pump-pressure pintle engine ignition experiment in different loading cases[J]. Aerospace Science and Technology, 2022, 127: 107732. doi: 10.1016/j.ast.2022.107732 [6] KANG D, HAN S, RYU C, et al. Design of pintle injector using Kerosene-LOx as propellant and solving the problem of pintle tip thermal damage in hot firing test[J]. Acta Astronautica, 2022, 201: 48-58. doi: 10.1016/j.actaastro.2022.08.029 [7] SHEN Chibing, ZHOU Rui. Experimental study on the combustion characteristics of LOX/LCH4 pintle injectors[J]. Fuel, 2023, 339: 126909. doi: 10.1016/j.fuel.2022.126909 [8] 李进贤, 岳春国, 侯晓, 等. 针栓式变推力火箭发动机内流场数值仿真研究[J]. 计算机仿真, 2009, 8: 49-52, 88. LI Jinxian, YUE Chunguo, HOU Xiao, et al. Numerical simulation of inner flow field of a pintle injector variable thrust rocket engine[J]. Computer Simulation, 2009, 8: 49-52, 88. (in Chinese doi: 10.3969/j.issn.1006-9348.2009.07.014LI Jinxian, YUE Chunguo, HOU Xiao, et al. Numerical simulation of inner flow field of a pintle injector variable thrust rocket engine[J]. Computer Simulation, 2009, 8: 49-52, 88. (in Chinese) doi: 10.3969/j.issn.1006-9348.2009.07.014 [9] 张连博, 毛晓芳, 汪凤山, 等. 针栓喷注式MMH/NTO推力室燃烧及传热数值仿真[J]. 推进技术, 2015, 36(10): 1487-1494. ZHANG Lianbo, MAO Xiaofang, WANG Fengshan, et al. Numerical simulation of pintle thruster combustion and heat transfer for MMH/NTO hypergolic bipropellant[J]. Journal of Propulsion Technology, 2015, 36(10): 1487-1494. (in ChineseZHANG Lianbo, MAO Xiaofang, WANG Fengshan, et al. Numerical simulation of pintle thruster combustion and heat transfer for MMH/NTO hypergolic bipropellant[J]. Journal of Propulsion Technology, 2015, 36(10): 1487-1494. (in Chinese) [10] 方昕昕, 沈赤兵, 张新桥. 针栓式喷注器锥形液膜破碎特性试验[J]. 航空动力学报, 2016, 31(12): 3004-3009. FANG Xinxin, SHEN Chibing, ZHANG Xinqiao. Experiment of breakup characteristics on conical sheets of pintle injectors[J]. Journal of Aerospace Power, 2016, 31(12): 3004-3009. (in ChineseFANG Xinxin, SHEN Chibing, ZHANG Xinqiao. Experiment of breakup characteristics on conical sheets of pintle injectors[J]. Journal of Aerospace Power, 2016, 31(12): 3004-3009. (in Chinese) [11] 方昕昕, 沈赤兵, 康忠涛. 无旋锥形液膜表面波不稳定性试验研究[J]. 推进技术, 2016, 37(10): 1893-1899. FANG Xinxin, SHEN Chibing, KANG Zhongtao. Experimental research of instability of surface wave on irrotational conical sheets[J]. Journal of Propulsion Technology, 2016, 37(10): 1893-1899. (in ChineseFANG Xinxin, SHEN Chibing, KANG Zhongtao. Experimental research of instability of surface wave on irrotational conical sheets[J]. Journal of Propulsion Technology, 2016, 37(10): 1893-1899. (in Chinese) [12] 方昕昕, 沈赤兵, 成鹏, 等. 针栓式喷注器雾化特性试验[J]. 航空动力学报, 2017, 32(8): 1853-1860. FANG Xinxin, SHEN Chibing, CHENG Peng, et al. Experiment on atomization characteristics of pintle injectors[J]. Journal of Aerospace Power, 2017, 32(8): 1853-1860. (in ChineseFANG Xinxin, SHEN Chibing, CHENG Peng, et al. Experiment on atomization characteristics of pintle injectors[J]. Journal of Aerospace Power, 2017, 32(8): 1853-1860. (in Chinese) [13] 方昕昕, 沈赤兵. 针栓式喷注器无旋锥形液膜线性不稳定分析[J]. 航空动力学报, 2017, 32(9): 2291-2298. FANG Xinxin, SHEN Chibing. Linear unstable analysis on irrotational conical sheets of pintle injectors[J]. Journal of Aerospace Power, 2017, 32(9): 2291-2298. (in ChineseFANG Xinxin, SHEN Chibing. Linear unstable analysis on irrotational conical sheets of pintle injectors[J]. Journal of Aerospace Power, 2017, 32(9): 2291-2298. (in Chinese) [14] FANG Xinxin, SHEN Chibing. Study on atomization and combustion characteristics of LOX/methane pintle injectors[J]. Acta Astronautica, 2017, 136: 369-379. doi: 10.1016/j.actaastro.2017.03.025 [15] ZHANG Yang, YU Nanjia, TIAN Hui, et al. Experimental and numerical investigations on flow field characteristics of pintle injector[J]. Aerospace Science and Technology, 2020, 103: 105924. doi: 10.1016/j.ast.2020.105924 [16] LEE Suji, KIM D, KOO J, et al. Spray characteristics of a pintle injector based on annular orifice area[J]. Acta Astronautica, 2020, 167: 201-211. doi: 10.1016/j.actaastro.2019.11.008 [17] LEE Suji, KOO J, YOON Y. Effects of skip distance on the spray characteristics of a pintle injector[J]. Acta Astronautica, 2021, 178: 471-480. doi: 10.1016/j.actaastro.2020.09.043 [18] KANG D, HWANG D, RYU C, et al. Analysis of pintle tip thermal damage in the combustion hot firing test with a 1.5-tonf class liquid-liquid pintle injector[J]. Journal of the Korean Society of Propulsion Engineers, 2020, 24(6): 1-9. doi: 10.6108/KSPE.2020.24.6.001 [19] 高志崇. 烃燃烧反应机理探讨[J]. 辽宁大学学报(自然科学版), 2002, 29(3): 266-271. GAO Zhichong. Mechanism of hydrocarbon combustion reaction[J]. Journal of Liaoning University (Natural Science Edition), 2002, 29(3): 266-271. (in ChineseGAO Zhichong. Mechanism of hydrocarbon combustion reaction[J]. Journal of Liaoning University (Natural Science Edition), 2002, 29(3): 266-271. (in Chinese) [20] 袁磊. 空气加热器高频燃烧不稳定维持机理研究[D]. 长沙: 国防科技大学, 2018. YUAN Lei. Study on maintenance mechanism of high frequency combustion instability of air heater[D]. Changsha: National University of Defense Technology, 2018. (in ChineseYUAN Lei. Study on maintenance mechanism of high frequency combustion instability of air heater[D]. Changsha: National University of Defense Technology, 2018. (in Chinese) [21] JIN Xuan, SHEN Chibing, ZHOU Rui, et al. Effects of LOX particle diameter on combustion characteristics of a gas-liquid pintle rocket engine[J]. International Journal of Aerospace Engineering, 2020, 2020: 8867199. [22] SON M, LEE K, KOO J. Characteristics of anchoring locations and angles for GOX/GCH4 flames of an annular pintle injector[J]. Acta Astronautica, 2020, 177: 707-713. doi: 10.1016/j.actaastro.2020.08.036 [23] 王凯, 雷凡培, 杨岸龙, 等. 径向孔形状对针栓式喷注器液膜下漏率的影响[J]. 航空学报, 2021, 42(6): 124384. WANG Kai, LEI Fanpei, YANG Anlong, et al. Effect of radial orifice shape on leakage rate of liquid sheet in pintle injector[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 124384. (in ChineseWANG Kai, LEI Fanpei, YANG Anlong, et al. Effect of radial orifice shape on leakage rate of liquid sheet in pintle injector[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 124384. (in Chinese) [24] 王凯, 雷凡培, 杨岸龙, 等. 针栓式喷注器液膜下漏率预估模型[J]. 航空动力学报, 2020, 35(10): 2223-2234. WANG Kai, LEI Fanpei, YANG Anlong, et al. Prediction model of leakage rate of liquid sheet in pintle injector[J]. Journal of Aerospace Power, 2020, 35(10): 2223-2234. (in ChineseWANG Kai, LEI Fanpei, YANG Anlong, et al. Prediction model of leakage rate of liquid sheet in pintle injector[J]. Journal of Aerospace Power, 2020, 35(10): 2223-2234. (in Chinese) -
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