动力舱冷却用排气引射混合管改进设计方法  

Improved design method of exhaust ejector mixing tube in cooling helicopter nacelle

作　　者：曹学伟[1] 余建祖[1] 谢永奇[1] 周懿[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航空动力学报》2010年第3期526-530,共5页Journal of Aerospace Power

摘　　要：对直升机动力舱冷却用的排气引射混合管的设计方法进行了研究,基于引射器特性方程和对引射特性影响因素的分析,参考某型直升机发动机排气系统,提出了针对直升机动力舱冷却用的排气引射混合管设计的改进方法——修正系数法.应用该方法,针对某型发动机动力舱冷却用排气引射混合管进行了设计,并与实验结果进行了对比,结果表明,该方法可以使设计效率提高30%,设计精度保持在5%以内,满足工程设计要求,具有工程应用价值.The conventional design methods of helicopter nacelle exhaust ejector mixing tube were introduced. Based on the characteristic equation and analysis of influence factors, and with a reference to nacelle exhaust systems of a helicopter, an improved design method of helicopter nacelle exhaust ejector mixing tube was established. Based on this improved method, a helicopter nacelle exhaust mixing tube was designed as an example. By comparing with other design results, this method could improve the design efficiency by 30% and maintain design accuracy within 5% to meet the engineering design requirements, demonstrating its availability and significance in engineering applications.

关 键 词：直升机 动力舱 排气引射器 弯曲混合管 引射系数 

分 类 号：V228.73[航空宇航科学与技术—飞行器设计]