基于变刚度特性的轴流压气机叶型重构方法研究  

A Reconstruction Method for Axial Compressor Blade Based on Variable Stiffness

作　　者：钟兢军[1] 康达[1] 王永亮[1] 刘子豪[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《推进技术》2017年第8期1857-1862,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金重点项目(51436002);辽宁省自然科学基金(2015020130);辽宁省高等学校创新团队支持计划资助项目(LT2015004);中央高校基本科研业务费专项资金资助(3132016016)

摘　　要：为能准确预估轴流压气机叶片在工作状态下的形状,基于流固耦合迭代策略,考虑离心力和气动力对叶片变形的作用,发展了一种适用于轴流压气机的叶型重构方法。在构型转化过程中,计入了叶片受力载荷随叶型变化的非线性效应以及叶片的变刚度特性。采用叶片变形后状态的受力载荷与刚度矩阵计算叶片节点位移,反复迭代修正热态叶片形状,最终获得满足精度要求的热态叶型数据。利用所提出的方法,对Stage 37的转子叶片进行了叶型重构,经20步迭代计算可获得最大残差小于10-4mm量级的热态叶型,通过与试验数据的对比分析,验证了重构算法的可靠性和工程实用性。A novel method for accurate estimation of axial compressor blade shape during operation is pre- sented based on fluid-structure coupling iterative algorithm, considering the effects of centrifugal and aerody- namic force on the blade deflection. During the blade configuration transformation, the blade nodal displace- ments are calculated using the force loadings and stiffness matrix of deformed blade. It is capable of accounting for the nonlinear force loadings and variable stiffness due to the blade deformation. The hot blade profile that satis- fies the required precision is obtained by modifying nodal coordinates iteratively. The method is used to recon- struct the operating shape of Stage 37 rotor blade. The hot blade shape can be obtained within 20 iteration steps. The maximum residual is less than 10-^-4mm. Comparison with experimental results shows that the reconstruction method is reliable and practical in engineering.

关 键 词：压气机 叶型重构 流固耦合 变刚度特性 

分 类 号：V260.5[航空宇航科学与技术—航空宇航制造工程]