直升机多路分流排气引射红外抑制系统气动特性计算  

Numerical research on aerodynamic characteristics inside single-stage ejection and multi-nozzles infrared system of helicopter

作　　者：潘丞雄[1] 张靖周[1] 单勇[1] 王先炜[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司中国直升机设计研究所,景德镇333001

出　　处：《航空动力学报》2010年第5期1025-1030,共6页Journal of Aerospace Power

摘　　要：针对直升机用单级引射、三路分流排气红外抑制系统进行了内部流场的三维数值模拟,在给定的模拟条件下,得到如下结论:①该红外抑制系统引射能力较强,三个支路引射混合管的引射流量比存在较大差异,总压恢复系数相差甚微;②分流喷管各支路通道喷口主流出口速度和压力基本一致,对各支路引射混合管引射能力影响最大的因素是次流流道的通畅程度;③三个支路引射混合管内主流核心速度和混合管出口温度衰减程度与其引射次流流量大小相关.Three-dimensional numerical simulation was carried out to investigate the internal aerodynamic characteristics insides the single-stage ejection and multi-nozzles infrared radiation suppressor used in the helicopter. Conclusions can be drawn as follows according to the simulation conditions：（1）This kind of infrared radiation suppressor has an impressive ability to pump secondary flow,the pumping ratios for three individual mixing duct differ obviously and the total pressure recovery coefficients are almost the same. （2）The primary flow velocities and pressures at multi-nozzles exit are the same,the important factor affecting the pumping ratio of the individual mixing duct is the secondary flow＇s smooth level.（3）The decay of the primary flow core velocity and temperature is relative to pumping ratio for three individual mixing ducts.

关 键 词：直升机 红外抑制器 多路分流喷管 内流气动特性 数值计算 

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] P722.5[天文地球—海洋科学]