航空发动机排气引射器推力性能研究  

Experiment and Simulation of Aviation Nozzle-ejector's Mixing and Thrust Capability

作　　者：文彬[1] 江勇[1] 梅飞[1] 方浩百[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038

出　　处：《空军工程大学学报（自然科学版）》2012年第1期23-27,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航空科学基金资助项目(20092244001)

摘　　要：根据发动机排气引射器流场的特征,建立了引射器内流场和排气系统外流流场的一体化三维数值模拟计算模型,得到了整个流场的基本参数;对引射器出口截面流场进行了理论分析,采用某型发动机引射器的尾流流场实验数据对模型进行了实验验证,理论分析和实验验证结果表明模型建立准确可靠。最后采用微元法,结合得到的流场参数计算了使用不同引射器时发动机的推力大小,并给出了各波瓣引射器相对于引射器1的推力损失情况。Based on the characteristic of aviation nozzle-ejector＇s wake-flow field,the modeling of study the flow in the nozzle-ejector and wake-flow field is conducted through numerical simulation,the whole flow field＇s basic parameter with the model is got.Analyzing the flow field of the nozzle-ejector＇s exhaust plane and validating the model through the experiment of certain aero-engine,the result indicates that the model can reflect the wake-flow field practically.At last,the thrust of every nozzle-ejector is calculated by the way of area element and the thrust loss of the lobe nozzle-ejector relative to the 1st nozzle-ejector is got.

关 键 词：引射器 流场计算 引射器出口截面 推力损失 实验验证 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]