流体喉部横流喷嘴的雾化特性
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摘要
为了研究横流喷嘴的雾化效果以及对发动机推力的影响,采用互击式直流喷嘴、逆向式直流喷嘴和水平式直流喷嘴进行了冷流试验.研究了不同试验工况下喷管出口喷雾场雾滴的索太尔平均直径与发动机的推力特性.研究结果表明:随着压比的增加,雾滴直径减小;相同的压比下,雾滴直径最小的喷射方案为喉扩喷射,雾化质量最好的喷嘴为互击式直流喷嘴;同时在喉扩喷射方案下,3种喷嘴的扼喉能力与推力比随着流量比的增加而提高.
In order to study atomization effects of the cross-flow injector and the influence on engine thrust,a series of cold-flow tests were performed using impinging injector,reverse injector and horizontal injector.The Sauter mean diameter of droplet in spray field at the exit of engine nozzle and thrust characteristics of engine were studied at different test cases.The test results indicate that with the increase of pressure ratio,the droplet diameter decreases;the injection case of the minimal droplet diameter is the throat and expanding section injection when the pressure ratio is given,and the injector of the best atomization quality is the impinging injector;meanwhile,the ability to control the throat and thrust ratio for three kinds of injectors increases with the increasing mass flow ratio under the throat and expanding section injection.
In order to study atomization effects of the cross-flow injector and the influence on engine thrust,a series of cold-flow tests were performed using impinging injector,reverse injector and horizontal injector.The Sauter mean diameter of droplet in spray field at the exit of engine nozzle and thrust characteristics of engine were studied at different test cases.The test results indicate that with the increase of pressure ratio,the droplet diameter decreases;the injection case of the minimal droplet diameter is the throat and expanding section injection when the pressure ratio is given,and the injector of the best atomization quality is the impinging injector;meanwhile,the ability to control the throat and thrust ratio for three kinds of injectors increases with the increasing mass flow ratio under the throat and expanding section injection.
引文
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[2]Martin A L.The acrodynamic variable nozzle[J].Journal of Aeronautical Sciences,1957,24(5):357-362.
[3]McArdle J G.Internal characteristics and performance of an aerodynamically controlled,variable discharge convergent nozzle[R].NACA TN 4312,1958.
[4]Blaszak J J,Fahrenholz F E.Rocket thrust control by gas injection[R].Cambridge,US:Massachusetts Institute of Technology,Naval Supersonic Laboratory Technial Report430,1960.
[5]Gunter F L,Fahrenholz F E.Final report on a study of rocket thrust control by Gas injection[R].Cambridge,US:Massachusetts Institute of Technology,Naval Supersonic Laboratory Technical Report 448,1961.
[6]郭常超,于新宇,李博,等.流体喉部推力特性实验[J].航空动力学报,2015,30(4):999-1007.GUO Changchao,YU Xinyu,LI Bo,et al.Experiment on thrust adjustment characteristics of fluidic nozzle throat[J].Journal of Aerospace Power,2015,30(4):999-1007.(in Chinese)
[7]Miller D N,Catt J A.Conceptual development of fixed-geometry nozzles using fluidic injection for throat-area control[R].AIAA 95-2603,1995.
[8]Deer K A.Summary of fiuidic thrust vectoring research conducted at NASA Langley Research Center[R].AIAA-2003-3800,2003.
[9]谢侃,刘宇,王一白,等.固体火箭发动机流体喉部喷管技术[M].北京:国防工业出版社,2015.
[10]张建华,谢侃.流体喉部喷管二次流矢量控制方案[J].北京航空航天大学学报,2012,38(3):309-313.ZHANG Jianhua,XIE Kan.Secondary flow thrust vector control study for fluidic thtoat nozzle[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(3):309-313.(in Chinese)
[11]杨道媛,马成良,孙宏魏,等.马尔文激光粒度分析仪粒度检测方法及其优化研究[J].中国粉体技术,2002,8(5):27-30.YANG Daoyuan,MA Chengliang,SUN Hongwei,et al.Research on particle size determination method and optimization of Malvern lazer particle analyzer[J].China Powder Science and Technology,2002,8(5):27-30.(in Chinese)
[12]甘舜仙.六分力试验台静态误差分析与调整[J].推进技术,1987(6):73-81.GAN Shunxian.Static error analysis and adjustment of six-component force test stand[J].Journal of Propulsion Technology,1987(6):73-81.(in Chinese)
[13]刘宏璇.六分力测试方法研究[D].南京:南京理工大学,2008.
[14]金如山.航空燃气轮机燃烧室[M].北京:宇航出版社,1985.
[15]Lefebvre A H.Gas turbine combustion[M].London:Talor&Francis,1999.
[16]张征,樊未军,杨茂林.双路离心式喷嘴雾化特性研究[J].工程热物理学报,2003,24(1):153-156.ZHANG Zheng,FAN Weijun,YANG Maolin.Experimental study on spray characteristics of dual-orifice pressureswirl atomizer[J].Journal of Engineering Thermophysics,2003,24(1):153-156.(in Chinese)
[17]张弛,张荣伟,徐国强,等.直射式双旋流空气雾化喷嘴的雾化效果[J].航空动力学报,2006,21(5):805-809.ZHANG Chi,ZHANG Rongwei,XU Guoqiang,et al.Experimental investigation on atomization of an air-blast atomizer with plain-orifice nozzle and dual-swirl cup[J].Journal of Aerospace Power,2006,21(5):805-809.(in Chinese)
[18]冯志鹏.气流中液滴破碎特性研究[D].南京:南京航空航天大学,2014.FENG Zhipeng.Research on the broken characteristics of droplets in the airflow[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2014.(in Chinese)