涡扇发动机二元喷管的红外光谱辐射特性实验  

Experiment on spectral infrared radiant characteristics of two-dimensional nozzles of turbofan engine

作　　者：罗明东[1] 吉洪湖[1] 黄伟[1] 蔡旭[1] 高潮[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2007年第4期394-398,共5页Journal of Propulsion Technology

摘　　要：为了获得涡扇发动机二元喷管的红外光谱辐射特性,分别测量了喷口面积相等而宽高比分别为1,4,8,12和16的二元喷管在3～5μm波段的红外光谱辐射特性,并与轴对称喷管进行了对比。喷管中的气流由主流燃气和次流空气组成,用以模拟涡扇发动机的喷管。结果表明,采用宽高比大于或等于4的二元喷管在绝大部分探测方向能够有效降低喷管的红外光谱辐射强度,但是在宽高比大于8以后二元喷管的红外光谱辐射强度不再随宽高比的增加而明显降低。The spectral infrared radiant intensities of 2D nozzles of turbofan engine are measured. The aspect ratio of the 2D nozzles are 1, 4, 8, 12 and 16, respectively. The measured spectral radiant intensities in the wave band of 3～5μm are presented and compared with that of axisymmetric nozzle with the same exit area. The flow inside the nozzle is composed of combustion gas stream in main channel and air stream in the secondary channel to simulate nozzles of turbofan engine. The resuits show that the 2D nozzle, with aspect ratio greater than four or equal to four can dramatically suppress infrared radiant of the nozzle in most orientation of detection. Its suppression effect increases with the increase of the aspect ratio. While further increasing aspect ratio after it is greater than 8 will no longer lead to obvious reducing of infrared spectral radiant intensity.

关 键 词：涡轮风扇发动机 二元喷管^+ 红外光谱辐射 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]