航天推进技术研究院主办
SONG Ge,LIAN Junwei,DING Zhenxiao.Performance study on standard aerosol generators for calibration of PDPA[J].Journal of Rocket Propulsion,2018,44(04):54-59.
用于PDPA校准的标准气溶胶发生器性能研究
- Title:
- Performance study on standard aerosol generators for calibration of PDPA
- 文章编号:
- 1672-9374(2018)04-0054-06
- 分类号:
- V432-34
- 文献标志码:
- A
- 摘要:
- 喷注器、喷嘴是低温液体火箭动力系统的核心部件,其雾化特性对燃烧效率和燃烧稳定性有直接的影响。通过激光相位多普勒测量系统(Phase Doppler Particle Analyzer简称PDPA)可以获得不同设计参数下喷雾场的粒径分布等重要数据。标准气溶胶发生器是校准和测试激光相位多普勒测量系统的基准源,通过其产生的标准粒子可以调校和修正系统测量误差。结合液体火箭动力系统喷注器雾化测量特点和散射粒子特性,对比分析了几种典型粒子发生技术,最终选择振动孔式单分散粒子发生器作为PDPA系统校准的基准源,并提出了一种标准气溶胶发生器的分析评定方法,通过该方法分别获得了发生器的均匀性、球形度、精度和稳定性等技术性能指标,证明该型发生器在喷注器雾化光学测量校准应用中具有适应性和可靠性。
- Abstract:
- The injector and nozzle are the core components of the cryogenic liquid rocket propulsion system, whose atomization properties have a direct effect on the efficiency and stability of combustion. Significant data such as the particle diameter distribution of the atomization field of different design parameters can be obtained by means of phase Doppler particle analyzer(PDPA). The standard aerosol generator is the reference source for the calibration and testing of PDPA. The standard particle produced by the standard aerosol generator can be used to calibrate and correct the system error. In combination with injector's atomization measuring characteristics and scattering particle's features of the liquid rocket power system, several typical particle generating technologies are compared and analyzed. On the basis of this, the vibration orifice monodisperse particle generator is selected as the reference source for calibration of PDPA, and an analysis and assessment method of the standard aerosol generator is proposed. With this method, the uniformity, sphericity, accuracy, stability and other technical performance indexes of the generator are obtained. The results prove that the generator is adaptable and reliable in the aspects of optical measurement and calibration of injector's atomization.
参考文献/References:
[1] POPE S B. Turbulent flows [M]. England: Cambridge University Press, 2000.
[2] 沈熊.激光多普勒测速技术及应用[M]. 北京: 清华大学出版社,2004.
[3] 程圣清, 宋连忠, 王珏. 氢氧火箭发动机预燃室喷注器特性研究[J]. 导弹与航天运载技术,1998(1):6-15.
[4] 黄兵, 张楠. 液体火箭发动机初始雾化液滴分布预测[J].火箭推进,2007,33(2):31-39.
HUANG Bing, ZHANG Nan. Prediction of droplet size distributions of primary atomization in liquid rocket engine [J]. Journal of rocket propulsion, 2007, 33(2): 31-39.
[5] 费俊.射流撞击雾化液滴运动过程与粒径分布特性的试验研究[J].火箭推进,2015,41(1):10-14.
FEI Jun. Experimental analysis on movement and size distribution of atomized droplets from impinging liquid jet [J]. Journal of rocket propulsion, 2015, 41(1): 10-14.
[6] 卢正永.气溶胶科学引论[M], 北京:原子能出版社,2000.
[7] 倪守邦. 国外气溶胶发生装置研制情况.冶金安全[J],1982(1):34-38.
[8] 杜斯特 F, 梅林A, 怀特洛J H.激光多普勒测速技术的原理和实践[M]. 北京:科学出版社,1992.
[9] 刘志军.高效空气过滤器测试用气溶胶发生器的研制及性能评价[D].天津:天津大学,2006.
[10] Thermo-Systems Incorporated(TSI). MDG-100 monosize droplet generator operation and service manual [M]. [S.l.]: TSI, 2006.
[11] Thermo-Systems Incorporated(TSI). Phase doppler particle analyzer(PDPA)laser Doppler velocimeter(LDV)operations manual [M]. [S.l.]: TSI, 2006.
[12] 沈熊等.应用激光相位-多普勒系统测量雾化液滴颗粒和流动特性[J].流体力学实验和测量,2000,14(2):54-60.
[13] 陈剑.应用激光相位多普勒技术对燃料喷雾特性的研究[D].上海:上海交通大学, 2004.
[14] 徐学哲, 赵卫雄, 方波, 等. 标准气溶胶发生系统的建立与性能评估[J].环境科学学报,2016.7(36):2355-2361.
相似文献/References:
[1]刘昌国,陈锐达,刘 犇,等.小推力空间液体火箭发动机夹气启动特性[J].火箭推进,2021,47(03):8.
LIU Changguo,CHEN Ruida,LIU Ben,et al.Start-up characteristics of low-thrust space liquid rocket engine with entrained gas[J].Journal of Rocket Propulsion,2021,47(04):8.
[2]熊剑,肖虹,李龙飞,等.基于增材制造的液氧/煤油推力室喷注器分析[J].火箭推进,2023,49(04):60.
XIONG Jian,XIAO Hong,LI Longfei,et al.Analysis on LOx/RP-1 thrust chamber injector for additive manufacturing[J].Journal of Rocket Propulsion,2023,49(04):60.
[3]孔维鹏,谢恒,王晓丽.基于激光选区熔化技术的大尺寸喷注器设计[J].火箭推进,2023,49(04):68.
KONG Weipeng,XIE Heng,WANG Xiaoli.Design of large dimensions injector based on selective laser melting technology[J].Journal of Rocket Propulsion,2023,49(04):68.
[4]白梅杉,於希乔,陆文杰,等.硝酸羟胺发动机喷注器特种流量分配方法[J].火箭推进,2023,49(05):99.
BAI Meishan,YU Xiqiao,LU Wenjie,et al.Injector flow distribution method of a hydroxylamine nitrate thruster[J].Journal of Rocket Propulsion,2023,49(04):99.
备注/Memo
收稿日期:2017-11-05
作者简介: 宋 戈(1987—),男,硕士,研究领域为液体火箭发动机流体试验技术及光学测量技术应用研究