摘要
采用有限元法,对平板叶片在不同鸟撞击角度下的非线性瞬态响应进行了数值分析研究.结果表明,平板叶片在不同撞击角度下的弯曲变形、到达最大变形的时间及残余变形随着撞击角度的增加而增大;平板叶片的扭转变形随着撞击角度的增加先增大后减少,撞击角度在小于30°及90°附近对平板叶片的扭转变形影响很小.
It is an important problem to calculate precisely the nonlinear transient responses inthe field of bird impact on the aeroengine blades. In order to analyze the influences of the im-pact angle on the response of the blades, the nonlinear transient responses of the plates underthe different impact angles are calculated and analyzed by using a simulate bird model and FEM(Finite Element Method). The results show that: (1) the curved deformation and the re-mained deformation of the plates increase with the impact angle; (2) the time in the maximumresponse of the plates also increase with the impact angle; (3) the twist deformation of theplates inceases firstly, and then descreases with the impact angle; (4) at the same time, it isfound that twist deformation of the plates is little when the impact angle is nearby 90°and be-low 30°.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
1996年第6期854-857,共4页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
叶片
瞬态响应
斜撞击
航空发动机
plates
transient response
oblique impact
nonlinear
