航天推进技术研究院主办
[1]张波涛,杨宝娥,杨岸龙,等.气液针栓喷注器液束撞击气膜破碎过程研究[J].火箭推进,2022,48(05):18-28.
ZHANG Botao,YANG Baoe,YANG Anlong,et al.Study on breakup process of impinging between liquid jet and gas sheet in gas-liquid pintle injector[J].Journal of Rocket Propulsion,2022,48(05):18-28.
点击复制
ZHANG Botao,YANG Baoe,YANG Anlong,et al.Study on breakup process of impinging between liquid jet and gas sheet in gas-liquid pintle injector[J].Journal of Rocket Propulsion,2022,48(05):18-28.
气液针栓喷注器液束撞击气膜破碎过程研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年05期
页码:
18-28
栏目:
目次
出版日期:
2022-10-25
- Title:
- Study on breakup process of impinging between liquid jet and gas sheet in gas-liquid pintle injector
- 文章编号:
- 1672-9374(2022)05-0018-11
- 分类号:
- V434.3
- 文献标志码:
- A
- 摘要:
- 为了全面认识气液针栓喷注器破碎过程,采用网格自适应加密技术、CLSVOF(coupled level-set and volume-of-fluid method)方法和SBES(stress-blended eddy simulation)湍流方法对气液针栓喷注器液束撞击气膜破碎过程进行数值仿真,获得了液束破碎过程的细节特征,并通过高速摄影试验结果验证了数值方法的准确性。以此为基础分析了液束撞击气膜的雾化模式、变形过程、流动特性和雾化角。结果表明:雾化模式根据局部动量比可分为振荡破碎、剪切破碎和液束主导的波动破碎 液束与气膜撞击后迎风面会向两侧运动,横截面先发展为“T”形,随后被展向拉伸为薄膜。液束前缘变形引起气流在液束两侧形成一系列涡结构,使得气液相互作用增强 雾化角主要受局部动量比影响,工况参数通过影响动量比而间接影响雾化角 认为选取中等局部动量比下的剪切雾化模式可以在获得较大雾化角的同时具有液滴粒径均匀且液滴空间分布均匀的特性。
- Abstract:
- In order to fully understand the breakup process of gas-liquid pintle injector,the breakup process of impinging liquid jet and gas sheet was simulated in gas-liquid pintle injector,based on the mesh adaptive refinement technology,CLSVOF(coupled level-set and volume-of-fluid method)method and SBES(stress-blended eddy simulation)turbulence method. The detailed structural characteristics of liquid jet breakup process were obtained. The accuracy of the numerical method was verified by the experimental results of high-speed photography. Based on the above,the spray pattern,deformation process,flow characteristic and spray angle were analyzed. The results show that the spray pattern can be divided into oscillation breaking,shearing breaking and wave breaking dominated by liquid jet according to the local momentum ratio. The cross section of the liquid jet develops into a "T" shape,which is then stretched laterally into a film shape. The deformation of the leading edge of the liquid jet causes the air flow to form a series of vortex structures on both sides,which enhances the interaction between the liquid jet and the gas sheet. The spray angle is mainly affected by the local momentum ratio,and operation parameters influence the spray angle through the momentum ratio. It is believed that the spray pattern when the middle local momentum ratio is selected can obtain a larger spray angle and has the characteristics of uniform droplets size and uniform spatial distribution of droplets.
参考文献/References:
[1] DRESSLER G,BAUER J. TRW pintle engine heritage and performance characteristics[C]//36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston,Virginia:AIAA,2000.
[2] CHENG P,LI Q L,XU S,et al. On the prediction of spray angle of liquid-liquid pintle injectors[J].Acta Astronautica,2017,138:145-151.
[3] FREEBERG J,HOGGE J. Spray cone formation from pintle-type injector systems in liquid rocket engines[C]//AIAA Scitech 2019 Forum. Reston,Virginia:AIAA,2019.
[4] BOETTCHER P A,DAMAZO J S,SHEPHERD J E,et al. Visualization of tranverse annular jets[C]//62nd Annual Meeting of the APS Division of Fluid Dynamics. Minneapolis,Minnesota:American Physical Society,2009.
[5] SON M,YU K,KOO J,et al. Effects of momentum ratio and Weber number on spray half angles of liquid controlled pintle injector[J].Journal of Thermal Science,2015,24(1):37-43.
[6] 成鹏. 变推力火箭发动机喷雾燃烧动态过程研究[D].长沙:国防科学技术大学,2018.
[7] 陈慧源,李清廉,成鹏,等.动量比及其调节方式对针栓喷注器喷雾特性的影响[J].物理学报,2019,68(20):204704.
[8] CHEN H Y,LI Q L,CHENG P. Experimental research on the spray characteristics of pintle injector[J].Acta Astronautica,2019,162:424-435.
[9] LEE S J,KIM D,KOO J,et al. Spray characteristics of a pintle injector based on annular orifice area[J].Acta Astronautica,2020,167:201-211.
[10] 石璞,朱国强,李进贤,等.液体火箭发动机针栓喷注器雾化燃烧技术研究进展[J].火箭推进,2020,46(4):1-13.
SHI P,ZHU G Q,LI J X,et al. Advances in atomized combustion technology research of pintle injector for liquid rocket engines[J].Journal of Rocket Propulsion,2020,46(4):1-13.
[11] 张波涛,李平,王凯,等.变推力液体火箭发动机中针栓喷注器研究综述[J].宇航学报,2020,41(12):1481-1489.
[12] 王凯,雷凡培,杨岸龙,等.针栓式喷注单元膜束撞击雾化混合过程数值模拟[J].航空学报,2020,41(9):91-105.
[13] 杨国华,张波涛,周立新,等.液气动量比对内混式直流气液喷嘴雾化特性影响[J].火箭推进,2019,45(5):66-73.
YANG G H,ZHANG B T,ZHOU L X,et al. Effects of momentum ratio on atomization characteristics of internal mixing gas-liquid injector[J].Journal of Rocket Propulsion,2019,45(5):66-73.
[14] 李佳楠,费俊,杨伟东,等.直流互击式喷注单元雾化特性准直接数值模拟[J].推进技术,2016,37(4):713-725.
[15] 王凯,杨国华,李鹏飞,等.基于Gerris的离心式喷嘴锥形液膜破碎过程数值模拟[J].推进技术,2018,39(5):1041-1050.
[16] 杨国华,王凯,张民庆,等.基于树形自适应网格的旋流液膜雾化过程仿真[J].推进技术,2018,39(3):556-564.
[17] SON M,YU K,RADHAKRISHNAN K,et al. Verification on spray simulation of a pintle injector for liquid rocket engine[J].Journal of Thermal Science,2016,25(1):90-96.
[18] RADHAKRISHNAN K,SON M,LEE K,et al. Effect of injection conditions on mixing performance of pintleinjector for liquid rocket engines[J].Acta Astronautica,2018,150:105-116.
[19] 张帝. 高精度有限体积格式及新型VOF自由界面捕捉算法[D].北京:清华大学,2015.
[20] OSHER S,SETHIAN J A. Fronts propagating with curvature-dependent speed:Algorithms based on Hamilton-Jacobi formulations[J].Journal of Computational Physics,1988,79(1):12-49.
[21] SUSSMAN M,PUCKETT E G. A coupled level set and volume-of-fluid method for computing 3D and axisymmetric incompressible two-phase flows[J].Journal of Computational Physics,2000,162(2):301-337.
[22] 张兆顺,崔桂香,许春晓. 湍流大涡数值模拟的理论和应用[M].北京:清华大学出版社,2008.
[23] MENTER F. Elements and applications of scale-resolving simulation methods in industrial CFD[M]//Direct and Large-Eddy Simulation IX,2015.
[24] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[25] NICOUD F,DUCROS F. Subgrid-scale stress modelling based on the square of the velocity gradient tensor[J].Flow,Turbulence and Combustion,1999,62:183-200.
备注/Memo
收稿日期:2021-02-28 修回日期:2021-04-27
基金项目:国家基础加强技术领域基金(2019-JCJQ-JJ-480)
作者简介:张波涛(1990—),男,博士,研究领域为液体火箭发动机喷雾燃烧技术。
更新日期/Last Update:
1900-01-01