航空发动机复合材料机匣叶片包容性研究  

INVESTIGATION ON BLADE CONTAINMENT OF AERO-ENGINE COMPOSITE CASE

作　　者：刘璐璐[1] 宣海军[1] 张娜[1] 

机构地区：[1]浙江大学工学部化工机械研究所,杭州310027

出　　处：《工程力学》2013年第B06期314-319,共6页Engineering Mechanics

基　　金：航空推进技术验证计划资助项目(APTD-11);浙江省自然科学基金项目(Y1090245);航空科学基金项目(20095276009);爆炸科学与技术国家重点实验室开放基金项目(KFJJ10-9M)

摘　　要：为研究复合材料机匣抵抗飞断叶片的包容能力及其损伤破坏机理,在高速旋转试验台上进行缩比模型试验,并采用显式瞬态动力学软件对复合材料机匣的包容机理进行了分析。通过分析叶片与机匣的撞击、击穿过程,研究了复合材料机匣包容机理;通过分析机匣壁厚对机匣破坏方式与包容能力的影响,获取了机匣壁厚与能量吸收的关系。结果表明:飞断叶片与复合材料机匣的撞击过程包含3次撞击,复合材料机匣在内壁与外壁的破坏方式显著不同;随壁厚增加,叶片发生严重的弯曲变形,且机匣能量吸收呈指数倍增加。To investigate the impact resistance and damage failure mechanisms of a composite aeroengine case, the subscale containment test was conducted on a high speed spin tester and numerical simulations were carried out using an explicit transient dynamic code, The impact process between the released blade and the composite case was investigated to obtain the containment mechanism of the composite case. The influences of the thickness on the failure mode and containment capacity were analyzed to study the correlation of the case thickness and the energy absorption. Containment process usually involves 3 continuous impacts. The failure modes are significantly different in the inner wall and the outer wall of the composite case. The released blade bends more severe and the energy absorption by the composite case increases exponentially with the increase of case thickness.

关 键 词：复合材料 叶片包容 包容性试验 数值仿真 航空发动机 

分 类 号：O347.3[理学—固体力学] V231.91[理学—力学]