摘要
为了自增压喷嘴更好地在航空活塞发动机上应用,在定容弹内对自增压喷嘴喷雾特性进行了试验研究。采用可视化技术结合Matlab图像处理程序,研究了RP-3航空煤油在不同背压、燃油温度和环境温度下的喷雾特性。结果表明:背压为0.1 MPa时的喷雾有明显的表面波和油线结构。背压从0.1 MPa增大至0.8 MPa,典型的中空锥喷雾转变成有大尺度涡流的中空锥喷雾,喷雾贯穿距离和喷雾面积的最大值分别减小了45%和55.3%。燃油温度的升高促进了喷雾蒸发有助于冷起动,喷雾贯穿距离、喷雾面积和喷雾锥角均在燃油温度为50℃时最小。在背压为0.1 MPa时,喷雾贯穿距离和喷雾面积随着环境温度升高先增大后减小,在环境温度为60℃和50℃分别有最大值67.3 mm和915.5 mm^(2),而喷雾锥角则随着环境温度升高而减小,在环境温度为90℃时达到最小值9.2°。
For the better application of the self-pressurized injector on aircraft piston engines,the spray characteristics of a self-pressurized injector was experimentally studied in a constant-volume vessel.Spray characteristics of RP-3 aviation kerosene under different ambient pressure,fuel temperature and ambient temperature were studied using visualization technology combining Matlab image processing program.Result showed that,the surface waves and fuel strings can be observed obviously under the ambient pressure of 0.1 MPa.With the ambient pressure increasing from 0.1 MPa to 0.8 MPa,the typical hollow cone spray was transformed into a hollow cone spray with large scale vortexes.The maximum spray penetration reduced by 45%,and the maximum spray area reduced by 55.3%,respectively.The increase of fuel temperature promotes spray evaporation to facilitate cold start.The spray penetration,area and cone angle were all minimum when the fuel temperature was 50℃.At the ambient pressure of 0.1 MPa,the spray penetration and area increased at first and then decreased with the increase of ambient temperature.The maximum spray penetration reached 67.3 mm at ambient temperature of 60℃,the maximum spray area reached 915.5 mm^(2) at ambient temperature of 50℃,respectively.The spray cone angle decreased with the increasing of ambient temperature,reaching the minimum value of 9.2°at ambient temperature of 90℃.
作者
楼煌强
魏民祥
刘锐
季昊成
杨海青
常诚
LOU Huangqiang;WEI Minxiang;LIU Rui;JI Haocheng;YANG Haiqing;CHANG Cheng(College of Energy and Power Engincering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;School of Mechanical and Power Engineering.Nanjing Tech Universit y,Nanjing 211816,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第12期2583-2592,共10页
Journal of Aerospace Power
基金
内燃机燃烧学国家重点实验室开放基金(K2020-05)
江苏省高等学校自然科学研究项目(20KJB470014)。
关键词
喷雾特性
自增压喷嘴
航空活塞发动机
RP-3航空煤油
油线
涡流
spray characteristics
self-pressurized injector
aircraft piston engines
RP-3 aviation kerosene
fuel strings
vortexes
