基于微型涡喷发动机的轴对称矢量喷管特性  

Research on Characteristics of Axisymmetric Vectoring Exhaust Nozzle Based on Micro Turbine Engine

作　　者：樊开岗 陈鑫[1] 董立伟[2] 张威江 FAN Kaigang;CHEN Xin;DONG Liwei;ZHANG Weijiang(Aeronautics Engineering College,Air Force Engineering University,Xi’an 710038,China;Beijing Aeronautical Engineering Technical Research Center,Beijing 100076,China)

机构地区：[1]空军工程大学航空工程学院,西安710038 [2]北京航空工程技术研究中心,北京100076

出　　处：《空军工程大学学报（自然科学版）》2020年第4期15-22,共8页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航空发动机进发排综合特性实验系统维修整治项目。

摘　　要：以微型涡喷发动机为平台进行了收敛型轴对称矢量喷管的数值特性模拟和实验验证。以雷诺时均方程为控制方程,采用SST k-ω模型研究了在微型涡喷发动机设计状态下轴对称矢量喷管不同几何偏转角下的俯仰推力矢量角特性、推力特性等,并基于该型微型涡喷发动机推力矢量特性实验对仿真模拟结果进行验证和补充。数值模拟和实验的结果表明,喷管出口几何偏转角在0°到20°之间,发动机推力损失较少,且俯仰推力、俯仰推力矢量角与几何偏角具有良好的线性关系。Taking a micro turbine engine as the platform,numerical simulation and experimental verification of convergent axisymmetric vectoring exhaust nozzles are performed.Regarding the Reynolds time-average equation as the governing equation,the SSTk-ω model is adopted to study the pitch and thrust vector angle characteristics and thrust characteristics of the axisymmetric vector nozzle at different geometric deflection angles in the design state of the micro turbine engine.And the simulation results are verified and supplemented based on the vector nozzle characteristics experiments of this type of turbojet engine.The numerical simulation and experimental results show that the nozzle's geometric deflection angle is at between 0°and 20°,the engine thrust loss is small,and there is a good linear relationship among the pitch thrust,the pitch thrust vector angle and the geometric declination.

关 键 词：轴对称矢量喷管 微型涡喷发动机 数值模拟 推力特性 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]