离心通风器壳体失效分析  

The Structure Failure Analysis of Centrifugal Ventilator Shell

作　　者：可成河 董本涵[2] 高鹏飞[2] 霍成民 廖连芳[2] 

机构地区：[1]沈阳黎明航空发动机(集团)公司军代表室,沈阳110042 [2]中国航空工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2002年第3期21-26,共6页Aeroengine

摘　　要：根据某发动机离心通风器6个故障件的破坏形貌分析结果以及简化模型的光弹性试验和有限元计算结果建立离心通风器壳体力学模型,并通过计算的名义应力探讨结构失效原因并提出排故措施。研究结果表明,由于壳体在油气混合环境中使用,其肋的转接台阶处具有高的应力集中、材料铸造表面粗糙、组织疏松等缺陷,助的截面尺寸公差太大等多种因素造成零件的可靠性降低。The shell mechanical analysis model was established depending upon the results of photoelasticity exper-memt and finite element calculation through observing the fracture topography of fault shells of centrifugal ventilator. The fatigue analysis of fault shell was conducted with nominal stress and service condition as well as fracture topography. The results showed that the shell failure behaved fatigue fracture, which was caused by high cycle load, harmful service environment and improper structure design.

关 键 词：离心通风器 失效分析 疲劳断裂 发动机 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]