降低涡轮动叶气动激振力的优化设计方法  

Optimization design method for reducing aerodynamic force of turbine rotor blade

作　　者：陈焕龙[1] 秦勇 蔡文哲[2] 王兵 颜廷松 CHEN Huanlong;QIN Yong;CAI Wenzhe;WANG Bing;YAN Tingsong(School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001 [2]北京动力机械研究所,北京100074

出　　处：《航空动力学报》2024年第11期143-151,共9页Journal of Aerospace Power

基　　金：重点实验室基金--军工院所稳定支持项目(WDZC312020030201);国家科技专项(J2019-Ⅱ-0016-0037)。

摘　　要：针对涡轮级叶列之间流场干扰诱发下游动叶非定常气动激振力的物理问题,提出了一种涡轮导叶与动叶联合匹配优化以降低动叶气动激振力的气动设计方法。研究表明:采用该方法不仅使得所研究涡轮动叶气动激振力的时均值下降8%,而且其他相位的动叶气流激振特性也获得改善,说明了该气动优化设计方法的可行性。此外,优化后的涡轮导叶具有明显的弯掠特征,弯掠导叶有助于降低下游动叶的非定常气动激振力,这是涡轮非定常气动设计技术对于“弯曲叶片”流动机理的新认识,非常值得开展更加深入的研究工作。In view of the physical problem of unsteady aerodynamic excitation force induced by flow interaction between turbine stage blades,an aerodynamic optimization design method for both turbine guide vanes and rotor blades was proposed and carried out.The research results indicated that not only the time-average aerodynamic force of the turbine rotor blade was reduced by about 8%,but also the aerodynamic excitation characteristics of other phases were improved for rotor blade.The results indicated the feasibility of this aerodynamic optimization design method.Moreover,the optimized guide vane had obvious curved and swept feature,allowing to reduce the unsteady aerodynamic excitation force of downstream rotor blade.This is a new understanding of the flow mechanism of“curved blades”in turbine unsteady aerodynamic design technology field,which is very worthy of further research.

关 键 词：非定常气动激振力 流动匹配 气动优化 尾迹干扰 激波 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] TK14[动力工程及工程热物理—热能工程]