纤维增强复合材料涡轮轴失效模式分析方法验证  

Verification of Failure Mode Analysis Method for Fiber Reinforced Composite Turbo-Shaft Structure

作　　者：沙云东 黄靖轩 骆丽 SHA Yun-dong;HUANG Jing-xuan;LUO Li(Liaoning Province Key Laboratory of Advanced Measurement and Test Technology of Aviation Propulsion Systems,School of Aeroengine,Shenyang Aerospace University,Liaoning Shenyang 110136,China)

机构地区：[1]沈阳航空航天大学航空发动机学院辽宁省航空推进系统先进测试技术重点实验室,辽宁沈阳110136

出　　处：《机械设计与制造》2024年第8期33-37,43,共6页Machinery Design & Manufacture

基　　金：中国航空发动机集团产学研合作项目(HFZL2018CXY019)。

摘　　要：针对连续纤维增强复合材料涡轮轴结构失效模式分析问题,基于宏-细观力学跨尺度分析方法,建立了与轴结构试验件尺寸相符合的有限元仿真计算模型,预测轴结构的危险位置并计算应变和位移响应,与试验结果进行对比验证。通过研究层合板主偏轴之间的关系应力的转化,将危险单元各个方向的宏观应力响应计算结果转化到细观力学RVE模型上,即为细观力学RVE模型受载情况;建立细观力学代表性体积元(RVE)模型,通过编程模拟实现模型的周期性边界条件,模拟复合材料轴结构损伤演化情况,并计算纤维增强复合材料应力响应,确定失效包线,结合损伤演化过程判别轴结构危险位置失效模式。开展复合材料失效模式验证试验,通过声发射及扫描电镜技术,实现对失效过程中不同失效模式的判别。将模拟仿真计算结果与试验结果对比分析,验证连续纤维增强复合材料涡轮轴结构失效模式分析方法的有效性。For continuous fiber reinforced composite turbo-shaft structural failure mode analysis,based on the macro-mechanics and meso-mechanics analysis method of cross-scale,a finite element simulation model with the same size of the shaft structure verification model is established,prediction and experimental verification of the dangerous position and the strain and displacement response response of composite shaft have been carried,and the principal stress response was calculated through the transformation of the principal-partial axial stress for the composite laminated plates,the macroscopic stress response calculation results of the dangerous elements in all directions were transformed into the microscopic mechanics RVE model,reflecting the microscopic mechanics load condition of the RVE model;a micro-mechanics representative volume element(RVE)model was established,through programming and simulation,the periodic boundary conditions of model were realized,the damage evolution of composite axial structure was simulated,the stress response of fiber reinforced composites was calculated,then the failure envelope was determined.The failure mode of dangerous position of shaft structure is identified according to the damage evolution process and the failure envelope.The failure mode verification test of composite shaft structure was carried out,different failure modes in the failure process were identified by acoustic emission and scanning electron microscopy techniques.The simulation results were compared with the test results,it verify the validity of the failure mode analysis method。

关 键 词：金属基复合材料 低压涡轮轴结构 失效模式分析方法 试验验证 

分 类 号：TH16[机械工程—机械制造及自动化] V232.2[航空宇航科学与技术—航空宇航推进理论与工程]