摘要
以国外某型先进无人机上使用的涡扇发动机为基础，缩比4．3倍得到轴对称收敛喷管AR0，并在出口面积相同的条件下改变喷口形状得到5组不同宽高比（W／H-1～16）的矩形喷管模型（AR1～AR16）．用傅立叶红外光谱仪对喷管与热喷流在3～5μm波段上的红外辐射进行了测试．研究发现，与轴对称喷管相比，矩形喷管减小了红外源的辐射，起到了明显的红外抑制作用，并且其红外抑制特性随着宽高比的增大是逐渐增强的．
Based on a fanjet currently used in an advanced unmanned vehicle,an axisymmetric nozzle AR0 of 4.3 expansion ratio was obtained. Under the same exit area, five rectangular convergent nozzle models （AR1-AR16）of different W/H（W/H= 1- 16） were experimentally investigated. The infrared radiation of nozzles and hot jet streams at 3-5μm were tested using Fourier Infrared Spectroscope. The results indicate that the magnitude of infrared radiation from rectangular nozzle is smaller than axisymmetric one,and the infrared suppressing effect of rectangular nozzles improves with the increase of aspect ratio.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第11期1820-1825,共6页
Journal of Aerospace Power
关键词
航空
航天推进系统
红外抑制
矩形喷管
大宽高比
双涵道
aerospace propulsion system
infrared suppressing
rectangular nozzle
aspect ratio
double channels
