Mechanism of “heat-acoustic-vortex” coupling for transverse unstable combustion in an O2/CH4 rectangle rocket combustor
-
摘要:
为了研究横向燃烧不稳定的潜在耦合机制，针对气氧/甲烷矩形火箭发动机开展了试验和数值模拟。试验采用高频压力传感器捕捉燃烧室内的动态压力特性，数值模拟采用应力混合涡模拟（SBES）和小火焰生成流（FGM）模型。结果表明：数值模拟可以准确捕捉到试验中的横向燃烧不稳定，数值计算结果在压力波形、主振频率和方均根幅值等方面与试验数据和理论结果吻合较好。对横向燃烧不稳定的驱动机理和瑞利指数进行了分析。燃烧室内流场特性表明，横向压力波会使氧气射流被周期性地“剥落”以及涡破碎，涡内燃料燃烧产生释热脉冲并耦合到燃烧室第一横向（1W）模态。瑞利因子分析表明，边缘喷嘴较中心喷嘴对横向燃烧不稳定具有更强的驱动特性。
Abstract:The potential coupling mechanism of transverse combustion instability in an O2/CH4 rectangle rocket combustor was investigated experimentally and numerically. High-frequency pressure sensors were employed to capture the dynamic pressure characteristics within the combustion chamber. Numerical simulations were conducted using the stress-blended eddy simulation (SBES) and flamelet-generated manifolds (FGM) methods. The results showed that the numerical simulation successfully predicted the transverse combustion instability observed experimentally. The numerical results, including pressure waveform, main frequency, and root mean square amplitude, were in good agreement with the experimental data and theoretical analysis. A comprehensive analysis of the driving mechanism and Rayleigh index of the transverse combustion instability was presented. Examination of the flow field characteristics in the combustion chamber revealed that the transverse pressure wave induced periodic ‘stripping’ of the oxygen jet and vortex disruption. Heat release pulses were generated during vortex fuel combustion and coupled with the first width (1W) mode. Rayleigh index analysis indicated that edge injectors exhibited stronger driving characteristics for transverse combustion instability compared with central injectors.
-
图 1 试验系统和矩形模型发动机构型
Figure 1. Experimental system, and the configuration of rectangular model rocket combustor
图 2 矩形模型燃烧室剖面图及尺寸（单位：mm）
Figure 2. Cut-away view of rectangular model combustor with detailed dimensions highlighted （unit：mm）
图 3 计算网格及初始条件和监测点分布
Figure 3. Schematic of computational grids with initial condition and boundary condition highlighted, and distribution of monitoring points
图 4 不同网格尺度下测点P1压力信号的PSD图
Figure 4. PSD plot of pressure signal in P1 at different grid scales
图 5 试验时序及监测点压力变化过程
Figure 5. Experimental time sequence and the pressure evolution process
图 8 一个振荡周期内压力、氧气质量分数、甲烷质量分数和释热率的演化过程
Figure 8. Evolution process of pressure, mass fraction of O2, mass fraction of CH4, and heat-release-rate within one instability cycle
图 9 监测点P1和P2处压力、释热率、涡量和甲烷质量分数振荡关系图
Figure 9. Interrelation among pressure, heat release rate, vorticity magnitude, and CH4 mass fraction at P1 and P2
表 1 热试车工况及试验结果
Table 1. Operating conditions and experimental results of hot-fire tests
参数 试验编号 1 2 3 $ p{ （\mathrm{O}}_{2}） $/MPa 2.06 2.08 2.05 $ \dot{m}{ （\mathrm{O}}_{2}） $/（g/s） 170 172 169 $ p{ （\mathrm{C}\mathrm{H}}_{4}） $/MPa 1.15 1.16 1.15 $ \dot{m}{ （\mathrm{C}\mathrm{H}}_{4}） $/（g/s） 100 101 100 pc/MPa 1.06 1.05 1.05 f/Hz 3033 3035 3029 $p'_{{\mathrm{RMS}}} $/MPa 0.195 0.196 0.188 
下载: 导出CSV
-
[1] 严宇, 王延涛, 李佳明, 等. 有声腔燃烧室的声学特性实验[J]. 航空动力学报, 2016, 31(7): 1785-1792. YAN Yu, WANG Yantao, LI Jiaming, et al. Experiment on acoustic characteristic of combustion chamber with acoustic resonators[J]. Journal of Aerospace Power, 2016, 31(7): 1785-1792. (in ChineseYAN Yu, WANG Yantao, LI Jiaming, et al. Experiment on acoustic characteristic of combustion chamber with acoustic resonators[J]. Journal of Aerospace Power, 2016, 31(7): 1785-1792. (in Chinese) [2] 楚威, 姜传金, 任永杰, 等. 自燃推进剂模型发动机纵向燃烧不稳定试验[J]. 航空动力学报, 2025, 40(5): 20230580. CHU Wei, JIANG Chuanjing, REN Yongjie, et al. Experiment on longitudinal conbustion instability of a hypergolic propellant model engine[J]. Journal of Aerospace Power, 2025, 40(5): 20230580. (in ChineseCHU Wei, JIANG Chuanjing, REN Yongjie, et al. Experiment on longitudinal conbustion instability of a hypergolic propellant model engine[J]. Journal of Aerospace Power, 2025, 40(5): 20230580. (in Chinese) [3] RAYLEIGH L. The explanation of certain acoustical phenomena1[J]. Nature, 1878, 18: 319-321. doi: 10.1038/018319a0 [4] 汪广旭, 谭永华, 陈建华, 等. 液体火箭发动机非稳态燃烧过程对其稳定性的影响[J]. 航空动力学报, 2019, 34(4): 929-936. WANG Guangxu, TAN Yonghua, CHEN Jianhua, et al. Effects of unsteady combustion process on combustion instability of liquid rocket engine[J]. Journal of Aerospace Power, 2019, 34(4): 929-936. (in ChineseWANG Guangxu, TAN Yonghua, CHEN Jianhua, et al. Effects of unsteady combustion process on combustion instability of liquid rocket engine[J]. Journal of Aerospace Power, 2019, 34(4): 929-936. (in Chinese) [5] MILLER K, SISCO J, NUGENT N, et al. Combustion instability with a single-element swirl injector[J]. Journal of Propulsion and Power, 2007, 23(5): 1102-1112. doi: 10.2514/1.26826 [6] YU Y C, SISCO J C, ROSEN S, et al. Spontaneous longitudinal combustion instability in a continuously-variable resonance combustor[J]. Journal of Propulsion and Power, 2012, 28(5): 876-887. doi: 10.2514/1.B34308 [7] SMITH R J. Computational investigations of high frequency acoustics and instabilities in a single-element rocket combustor[D]. West Lafayette, US: Purdue University, 2010. [8] YU Y C. Experimental and analytical investigations of longitudinal combustion instability in a continuously variable resonance combustor (CVRC)[D]. West Lafayette, US: Purdue University, 2009. [9] SISCO J C. Measurement and analysis of an unstable model rocket combustor[D]. West Lafayette, US: Purdue University, 2007. [10] POMEROY B, ANDERSON W. Transverse instability studies in a subscale chamber[J]. Journal of Propulsion and Power, 2016, 32(4): 939-947. doi: 10.2514/1.B35763 [11] MORGAN C J. Response of a gas-gas shear coaxial injector to transverse instability[D]. West Lafayette, US: Purdue University, 2012. [12] GRÖNING S, HARDI J S, SUSLOV D, et al. Injector-driven combustion instabilities in a hydrogen/oxygen rocket combustor[J]. Journal of Propulsion and Power, 2016, 32(3): 560-573. doi: 10.2514/1.B35768 [13] BROKOF P, GUZMÁN-IÑIGO J, MORGANS A S, et al. Injection-coupling instabilities in the BKD combustor: acoustic analysis of the isolated injectors[J]. AIAA Journal, 2023, 61(6): 2581-2590. doi: 10.2514/1.J062507 [14] BAI Xiao, CHENG Peng, LI Qinglian, et al. Effects of self-pulsation on combustion instability in a liquid rocket engine[J]. Experimental Thermal and Fluid Science, 2020, 114: 110038. doi: 10.1016/j.expthermflusci.2019.110038 [15] XUE Shuaijie, YANG Weidong, ZHOU Lixin, et al. Experimental investigation of self-excited combustion instabilities in a small Earth storable bipropellant rocket combustor[J]. Aerospace Science and Technology, 2020, 105: 106008. doi: 10.1016/j.ast.2020.106008 [16] YANG Anlong, LI Bin, YAN Yu, et al. Experimental of combustion instability in NTO/MMH impinging combustion chambers[J]. Chinese Journal of Aeronautics, 2020, 33(5): 1476-1485. doi: 10.1016/j.cja.2019.08.010 [17] 徐伯起, 郭康康, 任永杰, 等. 喷嘴式隔板与再生冷却肋片隔板对高频燃烧不稳定抑制效果的数值对比[J]. 航空动力学报, 2023, 38(12): 2948-2956. XU Boqi, GUO Kangkang, REN Yongjie, et al. Numerical comparative analysis of suppression effect of nozzlebaffle and regenerative cooling fin baffle on high-frequency unstable combustion[J]. Journal of Aerospace Power, 2023, 38(12): 2948-2956. (in ChineseXU Boqi, GUO Kangkang, REN Yongjie, et al. Numerical comparative analysis of suppression effect of nozzlebaffle and regenerative cooling fin baffle on high-frequency unstable combustion[J]. Journal of Aerospace Power, 2023, 38(12): 2948-2956. (in Chinese) [18] GARBY R, SELLE L, POINSOT T. Large-eddy simulation of combustion instabilities in a variable-length combustor[J]. Comptes Rendus Mécanique, 2013, 341(1/2): 220-229. [19] PANT T, HUANG Cheng, HAN Chao, et al. Flamelet modeling studies of a continuously variable resonance combustor: AIAA2016-1941[R]. Reston, US: AIAA, 2016. [20] GUO Kangkang, XU Boqi, REN Yongjie, et al. Three-dimensional numerical analysis of longitudinal thermoacoustic instability in a single-element rocket combustor[J]. Frontiers in Energy Research, 2022, 10: 835977. doi: 10.3389/fenrg.2022.835977 [21] SHIPLEY K J, ANDERSON W E, HARVAZINSKI M E, et al. A computational study of transverse combustion instability mechanisms: AIAA2014-3680 [R]. Reston, US: AIAA, 2014. [22] URBANO A, SELLE L, STAFFELBACH G, et al. Exploration of combustion instability triggering using large eddy simulation of a multiple injector liquid rocket engine[J]. Combustion and Flame, 2016, 169: 129-140. doi: 10.1016/j.combustflame.2016.03.020 [23] REN Yongjie, GUO Kangkang, FENG Songjiang, et al. Experimental and numerical investigation of transverse combustion instability in a rectangle multi-injector rocket combustor[J]. Acta Astronautica, 2023, 213: 215-230. doi: 10.1016/j.actaastro.2023.09.008 [24] GUO Kangkang, REN Yongjie, CHEN Peng, et al. Analysis of spontaneous longitudinal combustion instability in an O2/CH4 single-injector rocket combustor[J]. Aerospace Science and Technology, 2021, 119: 107209. doi: 10.1016/j.ast.2021.107209 [25] MENTER F. Stress-blended eddy simulation (SBES): a new paradigm in hybrid RANS-LES modeling[C]// Proceedings of the Progress in Hybrid RANS-LES Modelling: Papers Contributed to the 6th Symposium on Hybrid RANS-LES Methods. Strasbourg, France: Springer, 2018: 27-37. [26] PAN H, GENG Sajie, YANG Huan, et al. Influence of H2 blending on NOx production in natural gas combustion: mechanism comparison and reaction routes[J]. International Journal of Hydrogen Energy, 2023, 48(2): 784-797. doi: 10.1016/j.ijhydene.2022.09.251 [27] 任永杰, 丰松江, 聂万胜, 等. 单喷嘴火箭发动机高频燃烧不稳定的RANS和SBES数值模拟[J]. 推进技术, 2024, 45(7): 2305059. REN Yongjie, FENG Songjiang, NIE Wansheng, et al. Numerical simulation of RANS and SBES for high-frequency combustion instability of a single-element rocket engine[J]. Journal of Propulsion Technology, 2024, 45(7): 2305059. (in ChineseREN Yongjie, FENG Songjiang, NIE Wansheng, et al. Numerical simulation of RANS and SBES for high-frequency combustion instability of a single-element rocket engine[J]. Journal of Propulsion Technology, 2024, 45(7): 2305059. (in Chinese) [28] GUO Kangkang, REN Yongjie, TONG Yiheng, et al. Analysis of self-excited transverse combustion instability in a rectangular model rocket combustor[J]. Physics of Fluids, 2022, 34(4): 047104. doi: 10.1063/5.0086226 [29] ISSA R I. Solution of the implicitly discretized fluid flow equations by operator-splitting[J]. Journal of Computational Physics, 1986, 62(1): 40-65. doi: 10.1016/0021-9991(86)90099-9 [30] CULICK F E C, KUENTZMANN P. Unsteady motions in combustion chambers for propulsion systems[R]. California, US: California Institute of Technology Pasadena, 2006. [31] RICHECOEUR F. Experiments and numerical simulations of interactions between transverse acoustic modes and cryogenic flames[D]. Paris, France: Ecole Centrale Paris, 2006. [32] MCBRIDE B J. Computer program for calculation of complex chemical equilibrium compositions and applications[M]. Ohio, US: NASA Lewis Research Center, 1996. [33] HARVAZINSKI M E, ANDERSON W E, MERKLE C L. Analysis of self-excited combustion instabilities using two- and three-dimensional simulations[J]. Journal of Propulsion and Power, 2013, 29(2): 396-409. doi: 10.2514/1.B34732 -
点击查看大图
计量
- 文章访问数: 626
- HTML浏览量: 363
- PDF量: 52
- 被引次数: 0