动力舱冷却用排气引射混合管改进设计方法

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. 

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

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.