导叶约化中心位置对涡轮非定常气动计算的影响  

The effect of stator scaling center position on the turbine unsteady aerodynamic computation

作　　者：杨杰 宋友富 熊清勇 杨伟平 YANG Jie;SONG Youfu;XIONG Qingyong;YANG Weiping(Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Hunan Key Laboratory of Turbomachinery on Medium And Small Aero-Engine,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002

出　　处：《热科学与技术》2021年第4期386-394,共9页Journal of Thermal Science and Technology

摘　　要：针对工程上常用的基于叶片数约化的涡轮非定常计算方法,为了掌握导叶约化中心位置对于涡轮内部流动非定常计算结果的影响规律,对导叶前缘约化、导叶尾缘约化、不约化三个算例进行了非定常计算与对比分析。研究结果表明:导叶前缘约化方式对于涡轮气动性能时均值影响量级在1%以上,而导叶尾缘约化方式的影响不到前者的1/2;两种约化方式均能捕捉到导叶中的主要流动特征,但前缘约化方式导叶吸力面的吸力峰更强,导叶出口的气流角与马赫数更大;前缘约化方式转静之间的势扰动更强,导叶尾迹也更强,导叶尾缘与动叶前缘上的压力波动更强。根据研究结果,对涡轮性能与流动的影响来看,同导叶前缘约化方式相比,导叶尾缘约化方式非定常计算结果同无约化方式更接近,故若采用导叶约化进行非定常计算,应优先采用导叶尾缘约化方式。For the universally used blade-scaling unsteady computation method for turbine inner flows, in order to manage the effects of the stator blade scaling center position on the turbine inner flow unsteady computation results, unsteady computations and analysis are conducted on three cases including stator blade leading edge scaling(SQY), stator blade trailing edge scaling(SWY) and no scaling(SNO). The results show that the effect magnitude of SQY on the turbine performance time-averaged values is above 1%, but the SWY is under 1/2 of the former. Both two scaling methods can catch the main flow features in the stator, but for the SQY case, the suction peak on the stator suction side is stronger, and the flow angle and Mach number at the stator outlet are larger. For the SQY case, the potential disturbance and the stator wake are both stronger, and then the pressure fluctuation on the stator trailing area and the rotor leading area is stronger. From the view of the effect on the turbine performance and flow, compared to the stator leading edge scaling method, the computation results of the stator trailing edge scaling method is closer to the no scaling method. Therefore, when an unsteady computation by the stator scaling method is conducted, the stator trailing scaling one is preferential.

关 键 词：涡轮 非定常计算 导叶 约化中心位置 气动 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]