单级跨音压气机第1级可调静子在退喘过程中的气动力矩分析  

Aerodynamic moment analysis of first stage variable stator vanes of single⁃stage transonic compressor in surge exit process

作　　者：刘德龙 郭海宁 尹海宝 孟德君 LIU Delong;GUO Haining;YIN Haibao;MENG Dejun(Shenyang Engine Research Institute,Aero-Engine Corporation of China,Shenyang 110015,China)

机构地区：[1]中国航空发动机集团有限公司沈阳发动机研究所,沈阳110015

出　　处：《航空学报》2023年第24期69-82,共14页Acta Aeronautica et Astronautica Sinica

基　　金：国家级项目。

摘　　要：某单级跨音压气机在设计转速退喘过程中,第1级可调静子叶片(VSV)瞬间关闭且不受作动筒控制,从监控摄像头看到指示第1级可调静子角度状态的指针已经超出表盘关角度极限。紧接着第1级转子振幅增大,为退出该危险状态紧急降低压气机转速直至停车。为找出第1级可调静子异常关闭的原因,对其受到的气动力矩进行了分析。首先采用定常三维计算确定了第1级可调静子受到的气动力矩在压气机特性图上的分布,指出了气动力矩大的高风险三角区。其次通过三维非定常计算模拟了节气门快速打开后压气机流场以及气动力矩随时间的变化,揭示了可调静子异常关闭的原因。最后介绍了可避免这一危险情况的预防措施,这些措施在后续的单级压气机试验中被证明是有效的。In the process of the surge exit in a single-stage transonic compressor experiment at the design speed,the first stage Variable Stator Vanes(VSV)abnormally closed and could not be controlled by the actuation system.From the monitoring camera,it could be seen that the needle indicating the angle of the vanes exceeded the close limitation.Subsequently the vibration amplitude of the rotors amplified.In order to exit this dangerous situation,the ro⁃tational speed of the compressor was decreased until stop.To find out the mechanism of the abnormal close of the vanes,the aerodynamic moment acting on the vanes is analyzed.First,Computational Fluid Dynamics(CFD)steady simulations are carried out and the aerodynamic moment distribution on the compressor performance map is pre⁃sented.On this map,a high risk triangular area where the vanes withstand huge aerodynamic moment is pointed out.Then based on a CFD unsteady solution,the flow field and the aerodynamic moment variations versus time after the valve is opened are presented and the mechanism of the abnormal close of the vanes is revealed.Finally,some mea⁃surements to prevent this dangerous situation are presented,which are proven to be effective in the following singlestage compressor experiments.

关 键 词：单级压气机 跨音 可调静子叶片 异常关闭 气动力矩 压气机试验 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]