基于节点坐标修正和网格修匀的涡轮叶片冷态几何形状反算分析  

Back Calculation for Cold-state Geometric Shape of Turbine Blade Based on Modification of Nodal Coordinates and Mesh Smoothing

作　　者：孙树立[1,2] 汤槟 张明磊[1,2] 

机构地区：[1]北京大学力学与工程科学系,北京100871 [2]北京大学湍流与复杂系统国家重点实验室,北京100871

出　　处：《机械工程学报》2014年第10期143-148,共6页Journal of Mechanical Engineering

基　　金：国家自然科学基金(11172004;10772004);北京市自然科学基金(1102020)资助项目

摘　　要：涡轮叶片在工作状态下受到高温、高压及离心力的共同作用,其形状尺寸与冷态下有一定的差异。涡轮叶片的冷态尺寸反算,即根据叶片变形后的尺寸形状和载荷条件获得变形前的尺寸形状,是涡轮结构设计中不可或缺的重要组成部分。以有限元热-结构分析为基础,提出一种有效解决叶片冷态几何形状反算的迭代算法,主要通过节点坐标修正方式不断迭代来逼近叶片变形前的几何形状,并采用网格修匀技术保证修正后计算网格的质量。该算法流程实现简单,效率高,结果精确,可适用于发生复杂变形的结构,而且不依赖于所采用的有限元分析软件。应用所提出的算法针对某涡轮叶片结构成功地进行了其冷态几何形状的反算分析,验证了算法流程和其程序实现的实用性和可靠性。Turbine blade is subjected to combined action of high temperature,high pressure and centrifugal force under working state,and its geometric shape is different from the cold-state shape.As a key component of turbine design,back calculation for cold-state geometric shape of turbine blade,is to obtain undeformed geometric shape of turbine blade according to its deformed shape and load conditions.An iterative algorithm is presented based on finite element thermal and structural analysis to solve this problem effectively.The algorithm is to iteratively approach the undeformed geometric shape by modifying nodal coordinates,and guarantee the quality of modified mesh by smoothing technique.The algorithm is easily to implement with high efficiency and accuracy,applicable to structures with complex deformation behavior,and independent to finite element software to be applied.Back calculation for cold-state geometric shape of a turbine blade is successfully performed to verify the practicability and reliability of the presented algorithm and its implementation.

关 键 词：涡轮叶片 冷态 反算分析 节点坐标修正 网格修匀 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程] O242[理学—计算数学]