轴流压气机转子叶片预变形设计方法  

Design for pre-deformation of rotor blade for an axial compressor

作　　者：王永亮[1] 康达[1] 钟兢军[1] 刘子豪[1] 刘拓[2] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026 [2]国家电网公司研究室,北京100031

出　　处：《哈尔滨工程大学学报》2017年第3期392-396,共5页Journal of Harbin Engineering University

基　　金：国家自然科学基金项目(51606023;51436002);辽宁省自然科学基金项目(2015020130);中央高校基本科研业务费专项资金项目(3132016016)

摘　　要：压气机叶片在工作状态下受气动力和离心力的综合作用而产生的变形,给出了一种基于弱耦合迭代的叶片预变形设计方法。利用该方法以ANSYS与CFX为平台完成了对跨声速压气机叶片的预变形设计。研究结果表明:本文的预变形方法具有高效与高精度的特点,仅需20步迭代计算,即可获得最大残差小于10^(-5)mm量级的冷态叶型数据。该方法可用于轴流压气机及涡轮叶片的预变形设计,确保工作状态下的叶片实现设计构型。The compressor rotor blade may deform when subjected to the combined action of aerodynamic and cen-trifugal loads during operation. In this study,we present a blade pre-deformation design method based on loose cou-pling iteration. Utilizing this method,we derived a pre-deformation design for the blade of a transonic compressor with the help of ANSYS and CFX as our platform. The study results show that our proposed method is efficient and accurate,it is easy to obtain a cold-state blade profile with only 20 iteration steps,and the maximum residual is less than 10 5 mm. This method can be used for the pre-deformation design of an axial compressor and turbine blade to ensure an effective operational blade design configuration.

关 键 词：压气机 流固耦合 气动弹性 叶型设计 跨声速 预变形 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]