Simulation of liquid oxygen temperature and its influence on acoustic frequency of swirl injector
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摘要:
针对文献中采用离心喷嘴的氢氧预燃室热试车出现液膜声学相关频率的现象，采用两相流温度瞬态传热仿真计算了30 s热试车中喷嘴内液氧膜平均温度的变化过程。为节约计算资源和时间，采用Fluent多相流模型计算获得稳态等温速度场，采用二维轴对称传热模型调用两相流速度场和相分布结果进行流固耦合瞬态温度仿真。传热计算结果显示：喷嘴出口燃气温度对液氧膜温度有较为显著的影响。喷嘴出口气体温度升高50 K会导致液氧平均温度升高约2 K，喷嘴出口气体温度为105 K时，仿真计算得到的液氧平均温度数值与文献中经验修正值较为吻合，验证了其温度经验修正方法具有一定的合理性。模型计算结果能够解释固体热容对液氧加温作用导致喷嘴声学频率降低的现象。
Abstract:In view of the phenomenon of acoustic correlation frequency of liquid film appearing in hot-fire test of a hydrogen-oxygen preburner with swirl injectors in literature, the change process of average temperature of liquid oxygen film in injector during 30 s hot-fire test was calculated by transient thermal simulation of multiphase flow. In order to reduce the consumption of computational resources and time, multiphase model with Fluent was used to calculate the steady isothermal flow field, then, a two dimensional axisymmetric heat transfer model was used to call the velocity field and phase distribution results of Fluent to simulate the transient temperature. The results of heat transfer calculation showed that the gas temperature at the injector outlet had a significant effect on the liquid oxygen film temperature. The average temperature of liquid oxygen increased by about 2 K when the gas temperature increased by 50 K. The average temperature of liquid oxygen obtained by simulation was in good agreement with the empirical correction value in the literature when the injector outlet temperature was set to 105 K, which verified the reasonable temperature correction method. The calculation results can explain the phenomenon that the acoustic frequency of injector decreased duo to the effect of solid heat capacity on the heating of liquid oxygen.
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图 1 多相流模型网格边界及离心喷嘴主要尺寸
Figure 1. Mesh boundaries of multiphase model and major dimensions of the swirl injector
图 2 瞬态传热模型计算区域及边界
Figure 2. Computational domain and boundarys of transient heat transfer model
图 7 瞬态传热模型边界条件温度设置
Figure 7. Temperature setting of boundaries of transient heat transfer model
图 10 液膜、气涡及壁面平均温度对比
Figure 10. Comparison of average temperature of liquid film, gas core and wall
图 11 仿真液氧平均温度与文献经验修正值对比
Figure 11. Comparison of simulated average temperature of liquid oxygen and empirical correction value of literature
图 12 仿真温度与文献经验修正值计算频率对比
Figure 12. Comparison of frequencies caculated using simulated temperature and empirical correction value of literature
表 1 离心喷嘴几何参数
Table 1. Geometrical parameters of the swirl injector
参数 数值 氧喷嘴长度 L/mm 59.8 氧喷嘴半径 r0/mm 2.35 氢喷嘴内径 r1/mm 3 氢喷嘴外径 r2/mm 4.1 计算区域外径 r3/mm 8 切向孔直径 dt /mm 1.5 氧喷嘴缩进 Lr/mm 4 
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[1] RAYLEIGH J W S. The explanation of certain acoustical phenomena 1[J]. Nature,1878,18(455): 319-321. doi: 10.1038/018319a0 [2] LUX J,HAIDN O. Effect of recess in high-pressure liquid oxygen/methane coaxial injection and combustion[J]. Journal of Propulsion and Power,2009,25(1): 24-32. doi: 10.2514/1.37308 [3] ARMBRUSTER W,HARDI J S,SUSLOV D,et al. Experimental investigation of self-excited combustion instabilities with injection coupling in a cryogenic rocket combustor[J]. Acta Astronautica,2018,151: 655-667. doi: 10.1016/j.actaastro.2018.06.057 [4] 巴扎罗夫 V G. 液体喷嘴动力学[M]. 任汉芬, 孙纪国, 译. 北京: 中国宇航出版社, 1997. [5] BAZAROV V G,YANG V. Liquid-propellant rocket engine injector dynamics[J]. Journal of Propulsion and Power,1998,14(5): 797-806. doi: 10.2514/2.5343 [6] 杨立军,张向阳,葛明和. 敞口型离心喷嘴动力学特性理论分析[J]. 推进技术,2006,27(6): 497-500, 549.YANG Lijun,ZHANG Xiangyang,GE Minghe. Theoretical analysis of dynamics of open swirl injector[J]. Journal of Propulsion Technology,2006,27(6): 497-500, 549. (in Chinese) [7] 杨立军,富庆飞,王永涛,等. 多排切向通道敞口型离心喷嘴的动态特性研究[J]. 宇航学报,2006,27(5): 865-870.YANG Lijun,FU Qingfei,WANG Yongtao,et al. Investigation of dynamic of multi-row tangential channel opened swirl injector[J]. Journal of Astronautics,2006,27(5): 865-870. (in Chinese) [8] 杨立军,富庆飞. 喷嘴对供应系统到燃烧室压力振荡传递幅频特性的影响[J]. 航空动力学报,2008,23(2): 305-310.YANG Lijun,FU Qingfei. Effect of injector on pressure oscillation amplitude-frequency characteristics from pipeline to combustion chamber[J]. Journal of Aerospace Power,2008,23(2): 305-310. (in Chinese) [9] 杨立军,富庆飞,张向阳,等. 结构参数对敞口型离心喷嘴动态特性的影响[J]. 航空动力学报,2007,22(6): 864-868. doi: 10.3969/j.issn.1000-8055.2007.06.003YANG Lijun,FU Qingfei,ZHANG Xiangyang,et al. Study on influence of configuration parameter of open-end swirl injector on its dynamics[J]. Journal of Aerospace Power,2007,22(6): 864-868. (in Chinese) doi: 10.3969/j.issn.1000-8055.2007.06.003 [10] 杨立军,葛明和,张向阳. 液体离心喷嘴喷雾场动态特性的初步研究[J]. 航空动力学报,2005,20(6): 1083-1087. doi: 10.3969/j.issn.1000-8055.2005.06.032YANG Lijun,GE Minghe,ZHANG Xiangyang. Preliminary investigation on dynamic characteristics of swirl injector[J]. Journal of Aerospace Power,2005,20(6): 1083-1087. (in Chinese) doi: 10.3969/j.issn.1000-8055.2005.06.032 [11] 富庆飞,杨立军,屈元元,等. 气液同轴喷嘴缩进室动态特性均相流模型[J]. 航空动力学报,2010,25(8): 1918-1922. doi: 10.13224/j.cnki.jasp.2010.08.031FU Qingfei,YANG Lijun,QU Yuanyuan,et al. Investigation on dynamic characteristic of recessed region of a gas-liquid coaxial injector with homogeneous flow model[J]. Journal of Aerospace Power,2010,25(8): 1918-1922. (in Chinese) doi: 10.13224/j.cnki.jasp.2010.08.031 [12] FU Qingfei,YANG Lijun,WANG Xiangdong. Theoretical and experimental study of the dynamics of a liquid swirl injector[J]. Journal of Propulsion and Power,2010,26(1): 94-101. doi: 10.2514/1.44271 [13] ZONG N, YANG V. Dynamics of simplex swirl inject or s for cryogenic propellants at supercritical conditions[R]. AIAA-2004-1332, 2004. [14] ZONG Nan, YANG V. Supercritical fluid dynamics of pressure swirl injector with external excitations[R]. AIAA-2007-5458, 2007. [15] HUO Hongfa, ZONG Nan, YANG V. Cryogenic fluid dynamic response of swirl injector to external forcing at supercritical conditions[R]. AIAA-2009-233, 2009. [16] 富庆飞,杨立军,屈元元,等. 敞口型液体离心喷嘴动态特性数值模拟[J]. 航空动力学报,2010,25(9): 2132-2138.FU Qingfei,YANG Lijun,QU Yuanyuan,et al. Numerical simulation of dynamic characteristics of an open-end swirl injector[J]. Journal of Aerospace Power,2010,25(9): 2132-2138. (in Chinese) [17] BAI Xiao,LI Qinglian,CHENG Peng,et al. Investigation of self-pulsation characteristics for a liquid-centered swirl coaxial injector with recess[J]. Acta Astronautica,2018,151: 511-521. doi: 10.1016/j.actaastro.2018.07.002 [18] IM J H, YOUNGBIN Y, BAZAROV V G. Experimental study on self-pulsation a gas/liquid swirl coaxial injector in high pressure environment[R]. Daejeon, Korea: the 60th International Astronautical Congress, 2009. [19] TSOHAS J,HEISTER S D. Numerical simulations of liquid rocket coaxial injector hydrodynamics[J]. Journal of Propulsion and Power,2011,27(4): 793-810. doi: 10.2514/1.47761 [20] 张亚,潘刚,丁兆波,等. 离心喷嘴声学相关热试验频率分析与计算[J]. 航空动力学报,2022,37(7): 1478-1486.ZHANG Ya,PAN Gang,DING Zhaobo,et al. Analysis and calculation of acoustic frequency of swirl injector in hot-fire testing[J]. Journal of Aerospace Power,2022,37(7): 1478-1486. (in Chinese) -
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