旋流条件多参数耦合对横向射流煤油雾化特性影响

王波; 韩雨杉; 苗家铭; 任光明

doi:10.13224/j.cnki.jasp.20250300

旋流条件多参数耦合对横向射流煤油雾化特性影响

doi: 10.13224/j.cnki.jasp.20250300

南方科技大学力学与航空航天工程系，广东深圳 518055

基金项目: 国家科技重大专项（J2019-Ⅲ-0002-0045，J2019-Ⅲ-0005-0048）

详细信息

通讯作者:
王波（1988-），男，副研究员，博士，主要从事航空发动机燃烧、先进光学诊断方面的研究。E-mail：wangb6@sustech.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2025-06-25
- 网络出版日期: 2025-11-20

Multi-parameter coupling effects on atomization characteristics of kerosene jet in swirling crossflow

Department of Mechanics and Aerospace Engineering，Southern University of Science and Technology，Shenzhen Guangdong 518055，China

摘要

摘要:
航空发动机燃烧室工作环境复杂，旋流条件下多参数耦合作用对横向射流雾化特性的影响规律尚不清楚。采用激光粒度仪、平面激光测量的方法，获取了空气压力、空气温度、旋流器压降比、燃油温度、油气比等多参数交叉影响下的雾化粒径和油雾锥角数据，构建了包含韦伯数、雷诺数、奥内佐格数、旋流数等无量纲参数的半经验模型。研究发现：雾化粒径与气体韦伯数相关系数高达0.964，而韦伯数主要受进气压力及旋流器压降比影响；旋流强度对雾化粒径影响较小。油雾锥角与旋流强度的相关系数为0.866，说明燃油分布受旋流强度的影响较大，要显著强于动量比的影响。给定旋流条件下煤油雾化特性数据及半经验模型，可为航发燃烧室性能优化以及横向射流雾化喷嘴的设计提供支撑。
- 航空发动机燃烧室 /
- 横向射流喷射 /
- 旋流条件 /
- 多参数耦合影响 /
- 雾化特性
Abstract:
Due to the complex operating environment in aero-engine combustors, the laws governing the effects of multi-parameter coupling on the atomization characteristics of a kerosene jet in a swirling crossflow remain unclear. Utilizing a laser particle sizer and planar laser imaging techniques, data on droplet size and spray cone angle under the cross-effect of multiple parameters, including air pressure, air temperature, swirler pressure drop ratio, fuel temperature, and fuel-air ratio, were obtained. Semi-empirical models incorporating dimensionless parameters such as the Weber number, Reynolds number, Ohnesorge number, and swirl number were developed. The test results indicated that the correlation coefficient between the droplet size and the gas Weber number was as high as 0.964. The Weber number was mainly affected by the inlet pressure and the pressure drop ratio of the swirler, while the swirl intensity had a relatively minor impact on the droplet size. The correlation coefficient between the spray cone angle and the swirl intensity was 0.866, indicating that the fuel distribution was significantly affected by the swirl intensity, and this effect was notably stronger than that of the momentum ratio. The spray characteristic data and semi-empirical models established under swirling conditions could provide valuable support for optimizing aero-engine combustor performance and designing cross-flow atomizing nozzles.
- aero-engine combustor /
- jet in crossflow /
- swirling conditions /
- multi-parameter coupling effects /
- atomization characteristics

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图 1 旋流喷嘴结构示意图（单位：mm）

Figure 1. Detail structure of swirl nozzle （unit：mm）

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图 2 试验系统示意图

Figure 2. Schematic of the test system

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图 3 激光光学测量系统

Figure 3. Layout for optical measurements

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图 4 SMD试验结果

Figure 4. Test results of SMD

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图 5 工况变量的Spearman相关系数

Figure 5. Spearman coefficient of operating condition variables

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图 6 预测模型中各独立变量的Spearman相关系数

Figure 6. Spearman coefficient of the independent variables of the prediction model

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图 7 SMD预测分布

Figure 7. Distribution of predicted SMD

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图 8 SMD残差正态概率图

Figure 8. Normal probability plots of SMD residuals

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图 9 SMD模型的泛化能力检验

Figure 9. Test of the SMD model’s ability to generalize

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图 10 归一化PLIF与PMie信号对比

Figure 10. Comparison of normalized PLIF and PMie signals

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图 11 燃料分布瞬态演变

Figure 11. Instantaneous evolution of fuel distribution

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图 12 分布理论模型及锥角$ \theta $示意图验证

Figure 12. Validation of the theoretical model for distribution and the schematic diagram illustrating the cone angle $ \mathrm{\theta } $

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图 13 锥角自变量的Spearman系数

Figure 13. Spearman coefficient of the independent variables of the cone angle

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图 14 油雾锥角θ的预测分布

Figure 14. Distribution of predicted spray cone angle θ

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图 15 油雾锥角残差的正态概率分布

Figure 15. Normal probability plots of spray angle residuals

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图 16 喷雾锥角模型的泛化能力检验

Figure 16. Test of the spray angle model’s ability to generalize

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表 1 SN055工况条件表

Table 1. Operating conditions of SN055

序号	p_a/MPa	T_a/K	（Δp/p_a）/%	T_l/K	R
1	0.3	450	4	316	0.040
2	0.3	450	4	346	0.040
3	0.3	450	6	316	0.040
4	0.3	350	4	316	0.040
5	0.3	450	2	316	0.040
6	0.3	550	4	316	0.040
7	0.3	450	4	286	0.040
8	0.3	450	4	316	0.020
9	0.3	450	4	316	0.050
10	0.5	450	4	316	0.040
11	0.1	450	4	316	0.040
12	0.4	490	6	331	0.020
13	0.4	490	6	331	0.050
14	0.2	490	6	331	0.05
15	0.4	410	6	331	0.05
16	0.4	490	2	301	0.02
17	0.4	410	6	301	0.02
18	0.2	410	2	301	0.05
19	0.4	490	2	301	0.05
20	0.2	410	2	301	0.02
21	0.2	410	6	301	0.02
22	0.4	410	2	331	0.05
23	0.4	410	2	301	0.05
24	0.2	490	2	301	0.05
25	0.2	490	6	301	0.05
26	0.4	490	2	331	0.02
27	0.4	410	2	331	0.02
28	0.2	410	6	301	0.05
29	0.4	410	6	301	0.05
30	0.4	410	6	331	0.02
31	0.2	410	6	331	0.02
32	0.4	490	6	301	0.02
33	0.2	490	2	331	0.02
34	0.2	490	6	331	0.02
35	0.2	410	2	331	0.02
36	0.2	490	6	301	0.02
37	0.4	490	6	301	0.05
38	0.2	410	6	331	0.05
39	0.4	490	2	331	0.05
40	0.2	410	2	331	0.02
41	0.2	490	2	301	0.02
42	0.4	410	2	301	0.02
43	0.2	490	2	331	0.05
44	0.1	303	4	316	0.04
45	0.8	550	4	316	0.05
46	0.2	340	4	316	0.04
47	0.45	500	4	316	0.04

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表 2 工况水平度取值

Table 2. Values of the level for operating conditions

工况条件	水平度
p_a/MPa	0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7, 0.8
T_a/K	303, 340, 350, 410, 450, 490, 500, 550
（Δp/p_a）/%	2, 4, 6
T_l/K	286, 301, 316, 331, 346
R	0.02, 0.04, 0.05

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表 3 SMD相关变量系数值及方差

Table 3. SMD’s values of the coefficients and the variance R²

系数	数值
A	5.6689
B	−0.7739
C	0.0240
D	−0.0723
E	−0.0061
F	−0.4014
R²	0.983
平均误差/%	8.22

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表 4 锥角相关系数值及方差

Table 4. Cone angle’s values of the coefficients and the variance R²

参数	数值
$ \alpha $	6.274
$ \beta $	4.140
$ \gamma $	0.125
$ \delta $	−0.091
$ \varepsilon $	0.022
$ {R}^{2} $	0.945
平均误差/%	9.84

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参考文献(44)

[1]	陈炫午, 曾青华, 甘晓华. 航空发动机高温升燃烧室技术分析[J]. 推进技术, 2023, 44(2): 2208054. CHEN Xuanwu, ZENG Qinghua, GAN Xiaohua. Analysis of combustion technology of high temperature rise for aero engines[J]. Journal of Propulsion Technology, 2023, 44(2): 2208054. (in Chinese CHEN Xuanwu, ZENG Qinghua, GAN Xiaohua. Analysis of combustion technology of high temperature rise for aero engines[J]. Journal of Propulsion Technology, 2023, 44(2): 2208054. (in Chinese)
[2]	王晓洁, 王少林, 王凯兴, 等. 高温高速气流中航空煤油横向射流实验研究[J]. 推进技术, 2023, 44(5): 2204002. WANG Xiaojie, WANG Shaolin, WANG Kaixing, et al. Experimental study on jet in crossflow of aviation kerosene in high temperature and high speed airflow[J]. Journal of Propulsion Technology, 2023, 44(5): 2204002. (in Chinese WANG Xiaojie, WANG Shaolin, WANG Kaixing, et al. Experimental study on jet in crossflow of aviation kerosene in high temperature and high speed airflow[J]. Journal of Propulsion Technology, 2023, 44(5): 2204002. (in Chinese)
[3]	KRZECZKOWSKI S A. Measurement of liquid droplet disintegration mechanisms[J]. International Journal of Multiphase Flow, 1980, 6(3): 227-239. doi: 10.1016/0301-9322(80)90013-0
[4]	BEHZAD M, ASHGRIZ N, KARNEY B W. Surface breakup of a non-turbulent liquid jet injected into a high pressure gaseous crossflow[J]. International Journal of Multiphase Flow, 2016, 80: 100-117. doi: 10.1016/j.ijmultiphaseflow.2015.11.007
[5]	LI Xiaoyi, SOTERIOU M C. Detailed numerical simulation of liquid jet atomization in crossflow of increasing density[J]. International Journal of Multiphase Flow, 2018, 104: 214-232. doi: 10.1016/j.ijmultiphaseflow.2018.02.016
[6]	MASHAYEK A, BEHZAD M, ASHGRIZ N. Multiple injector model for primary breakup of a liquid jet in crossflow[J]. AIAA Journal, 2011, 49(11): 2407-2420. doi: 10.2514/1.J050623
[7]	朱英, 黄勇, 王方, 等. 横向气流中的液体圆形射流破碎实验[J]. 航空动力学报, 2010, 25(10): 2261-2266. ZHU Ying, HUANG Yong, WANG Fang, et al. Experiment on the breakup of round liquid jets in cross airflows[J]. Journal of Aerospace Power, 2010, 25(10): 2261-2266. (in Chinese ZHU Ying, HUANG Yong, WANG Fang, et al. Experiment on the breakup of round liquid jets in cross airflows[J]. Journal of Aerospace Power, 2010, 25(10): 2261-2266. (in Chinese)
[8]	王雄辉, 黄勇, 王方, 等. 横向气流中液体圆柱射流的破碎特性和表面波现象[J]. 航空动力学报, 2012, 27(9): 1979-1987. WANG Xionghui, HUANG Yong, WANG Fang, et al. Breakup characteristics and surface wave phenomenon of round liquid jets in crossflows[J]. Journal of Aerospace Power, 2012, 27(9): 1979-1987. (in Chinese WANG Xionghui, HUANG Yong, WANG Fang, et al. Breakup characteristics and surface wave phenomenon of round liquid jets in crossflows[J]. Journal of Aerospace Power, 2012, 27(9): 1979-1987. (in Chinese)
[9]	王雄辉, 黄勇, 王方, 等. 横向气流中液体射流袋式破碎机理[J]. 推进技术, 2012, 33(2): 198-204. WANG Xionghui, HUANG Yong, WANG Fang, et al. Bag breakup of round liquid jets in crossflow[J]. Journal of Propulsion Technology, 2012, 33(2): 198-204. (in Chinese WANG Xionghui, HUANG Yong, WANG Fang, et al. Bag breakup of round liquid jets in crossflow[J]. Journal of Propulsion Technology, 2012, 33(2): 198-204. (in Chinese)
[10]	WANG Xionghui, HUANG Yong, WANG Shaolin, et al. Bag breakup of turbulent liquid jets in crossflows[J]. AIAA Journal, 2012, 50(6): 1360-1366. doi: 10.2514/1.J051451
[11]	刘涛. 航空煤油雾化特性实验研究[D]. 合肥: 中国科学技术大学, 2018. LIU Tao. Experimental study on atomization characteristics of aviation kerosene[D]. Hefei: University of Science and Technology of China, 2018. (in Chinese LIU Tao. Experimental study on atomization characteristics of aviation kerosene[D]. Hefei: University of Science and Technology of China, 2018. (in Chinese)
[12]	李春. 超声速横向气流中液体射流表面波及射流破碎机理研究[D]. 长沙: 国防科技大学, 2020. LI Chun. Study on the surface wave and jet breakup mechanism of liquid jet in supersonic cross-flow[D]. Changsha: National University of Defense Technology, 2020. (in Chinese LI Chun. Study on the surface wave and jet breakup mechanism of liquid jet in supersonic cross-flow[D]. Changsha: National University of Defense Technology, 2020. (in Chinese)
[13]	仝毅恒. 横向气流中液体射流喷注特性和破碎过程研究[D]. 长沙: 国防科学技术大学, 2012. TONG Yiheng. Study on injection characteristics and crushing process of liquid jet in transverse airflow[D]. Changsha: National University of Defense Technology, 2012. (in Chinese TONG Yiheng. Study on injection characteristics and crushing process of liquid jet in transverse airflow[D]. Changsha: National University of Defense Technology, 2012. (in Chinese)
[14]	WU Peikuan, KIRKENDALL K A, FULLER R P, et al. Spray structures of liquid jets atomized in subsonic crossflows[J]. Journal of Propulsion and Power, 1998, 14(2): 173-182. doi: 10.2514/2.5283
[15]	SALLAM K A, AALBURG C, FAETH G M. Breakup of round nonturbulent liquid jets in gaseous crossflow[J]. AIAA Journal, 2004, 42(12): 2529-2540. doi: 10.2514/1.3749
[16]	FU Qingfei, YAO Muwei, YANG Lijun, et al. Atomization model of liquid jets exposed to subsonic crossflows[J]. AIAA Journal, 2020, 58(5): 2347-2351. doi: 10.2514/1.J059132
[17]	曾夜明. Ma2.1来流条件下液体横向射流喷雾特性试验研究[D]. 长沙: 国防科学技术大学, 2015. ZENG Yeming. Experimental study on spray characteristics of liquid transverse jet under the condition of Ma2.1 incoming flow[D]. Changsha: National University of Defense Technology, 2015. (in Chinese ZENG Yeming. Experimental study on spray characteristics of liquid transverse jet under the condition of Ma2.1 incoming flow[D]. Changsha: National University of Defense Technology, 2015. (in Chinese)
[18]	SURYA PRAKASH R, SINHA A, TOMAR G, et al. Liquid jet in crossflow-effect of liquid entry conditions[J]. Experimental Thermal and Fluid Science, 2018, 93: 45-56. doi: 10.1016/j.expthermflusci.2017.12.012
[19]	AMIGHI A, ESLAMIAN M, ASHGRIZ N. Trajectory of a liquid jet in high pressure and high temperature subsonic air crossflow [C]// International conference on liquid atomization and spray systems. Vail, US: ICLASS, 2009: 225-231.
[20]	HWANG Y S, JIN Y I. The penetration characteristics of normally injected kerosene liquid jet in high weber number flow: AIAA 2009-5156[R]. Daejeon, Korea: 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009.
[21]	STENZLER J N, LEE J G, SANTAVICCA D A. Penetration of liquid jets in a crossflow [C]// 41st Aerospace Sciences Meeting and Exhibit. Reno, US: AIAA, 2003: 1327.
[22]	MASUDA B J, MCDONELL V G. Penetration of a recessed distillate liquid jet into a crossflow at elevated pressure and temperature [C]// International conference on liquid atomization and spray systems. Kyoto, Japan: ICLASS, 2006: 275.
[23]	BELLOFIORE A, CAVALIERE A, RAGUCCI R. Air density effect on the atomization of liquid jets in crossflow[J]. Combustion Science and Technology, 2007, 179(1/2): 319-342.
[24]	LI Lin, LIN Yuzhen, XUE Xin, et al. Injection of liquid kerosene into a high-pressure subsonic air crossflow from normal temperature to elevated temperature[C]//Turbo Expo: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2012, 44687: 877-884.
[25]	PATIL S, SAHU S. Liquid jet core characterization in a model crossflow airblast atomizer[J]. International Journal of Multiphase Flow, 2021, 141: 103688. doi: 10.1016/j.ijmultiphaseflow.2021.103688
[26]	PATIL S, SAHU S. Insight into liquid jet atomization in a swirling crossflow airblast injector: application of a multi-directional imaging technique[J]. International Journal of Multiphase Flow, 2023, 158: 104279. doi: 10.1016/j.ijmultiphaseflow.2022.104279
[27]	TAMBE S, JENG S M. A study of liquid jets injected transversely into a swirling crossflow[C]//21st Annual Conference on Liquid Atomization and Spray Systems. Orlando, US: ILASS Americas, 2008: 18-21.
[28]	SIKRORIA T, KUSHARI A. Effect of cross-flow swirl on the trajectory of spray in an annular passage[J]. Journal of Engineering for Gas Turbines and Power, 2021, 143(5): 051017. doi: 10.1115/1.4049378
[29]	SIKRORIA T, KUSHARI A. Experimental analysis and phenomenological model for liquid jet breakup in swirling flow of air[J]. Journal of Engineering for Gas Turbines and Power, 2019, 141(9): 091015. doi: 10.1115/1.4044060
[30]	SIKRORIA T, KUSHARI A, SYED S, et al. Experimental investigation of liquid jet breakup in a cross flow of a swirling air stream[J]. Journal of Engineering for Gas Turbines and Power, 2014, 136(6): 061501. doi: 10.1115/1.4026244
[31]	PATIL S, SAHU S. Air swirl effect on spray characteristics and droplet dispersion in a twin-jet crossflow airblast injector[J]. Physics of Fluids, 2021, 33(7): 073314. doi: 10.1063/5.0054430
[32]	PATIL S, SAHU S. Breakup dynamics and near nozzle spray fluctuations in a twin-jet cross-flow airblast atomizer[J]. Atomization and Sprays, 2019, 29(3): 217-250. doi: 10.1615/AtomizSpr.2019030177
[33]	PATIL S, SAHU S. Spray characterization in a multi-jet airblast injector with swirling air crossflow[J]. Aerospace Science and Technology, 2023, 132: 108085. doi: 10.1016/j.ast.2022.108085
[34]	BECKER J, HASSA C. Liquid fuel placement and mixing of generic aeroengine premix module at different operating conditions[J]. Journal of Engineering for Gas Turbines and Power, 2003, 125(4): 901-908. doi: 10.1115/1.1587741
[35]	BECKER J, HEITZ D, HASSA C. Spray dispersion in a counter-swirling double-annular air flow at gas turbine conditions[J]. Atomization and Sprays, 2004, 14(1): 15-36. doi: 10.1615/AtomizSpr.v14.i1.20
[36]	BEER J M, CHIGIER N A. Combustion aerodynamics[M]. London: Applied Science Publishers LTD, 1972.
[37]	倪计民, 杜倩颖, 周英杰, 等. DoE在高压共轨柴油机优化设计中的应用[J]. 内燃机学报, 2009, 27(3): 231-236. NI Jimin, DU Qianying, ZHOU Yingjie, et al. Application of DoE in common rail diesel engine optimization design[J]. Transactions of CSICE, 2009, 27(3): 231-236. (in Chinese NI Jimin, DU Qianying, ZHOU Yingjie, et al. Application of DoE in common rail diesel engine optimization design[J]. Transactions of CSICE, 2009, 27(3): 231-236. (in Chinese)
[38]	LEFEBVRE A H, MCDONELL V G. Atomization and sprays[M]. Boca Raton: CRC press, 2017.
[39]	FANG Chuanyu, LIU Yushuai, WANG Shaolin, et al. Aerodynamic effect on atomization characteristics in a swirl cup airblast fuel injector[J]. Physics of Fluids, 2023, 35(10): 103319. doi: 10.1063/5.0170317
[40]	PIANTADOSI J, HOWLETT P, BOLAND J. Matching the grade correlation coefficient using a copula with maximum disorder[J]. Journal of Industrial & Management Optimization, 2007, 3(2): 305-312.
[41]	邓甜, 李佳周, 陈伟. 剪切气流中无黏液体横向射流破碎机理[J]. 航空学报, 2021, 42(7): 124464. DENG Tian, LI Jiazhou, CHEN Wei. Breakup mechanism of inviscid liquid transverse jet in shear airflow[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(7): 124464. (in Chinese DENG Tian, LI Jiazhou, CHEN Wei. Breakup mechanism of inviscid liquid transverse jet in shear airflow[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(7): 124464. (in Chinese)
[42]	邓甜, 李佳周, 陈伟. 黏性液体横向射流破碎机理[J]. 航空学报, 2022, 43(3): 125130. DENG Tian, LI Jiazhou, CHEN Wei. Breakup mechanism of viscous liquid transverse jet[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(3): 125130. (in Chinese DENG Tian, LI Jiazhou, CHEN Wei. Breakup mechanism of viscous liquid transverse jet[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(3): 125130. (in Chinese)
[43]	MIAO Jiaming, WANG Bo, REN Guangming, et al. Mean droplet size prediction of twin swirl airblast nozzle at elevated operating conditions[J]. Energies, 2024, 17(20): 5027. doi: 10.3390/en17205027
[44]	SHIN D, SATIJA A, LUCHT R P. Spray characteristics of standard and alternative aviation fuels at high ambient pressure conditions[J]. Experimental Thermal and Fluid Science, 2022, 130: 110511. doi: 10.1016/j.expthermflusci.2021.110511