摘要
对航空发动机风扇叶片振动适航符合性设计方法开展了研究。采用非均匀有理B样条实现风扇叶片型线的设计,通过各截面型线质心实现风扇叶片积叠成型;建立榫头的草图,拉伸生成风扇叶片的圆弧榫;考虑强度、振动特性,实现伸根段的设计。从振动适航条款CCAR 33.83的要求出发,给出了风扇叶片振动符合性的验证方法,基于建立的风扇叶片模型,采用有限元方法对风扇叶片的振动特性和振动应力进行计算。计算结果表明,在整个飞行包线环境下,该风扇叶片的振动特性和振动应力水平满足振动的适航条款要求,为风扇叶片的振动符合性设计与验证提供了依据。
An approach for vibration airworthiness compliance of aeroengine fan blade is investigated.The fan blade is designed by the parametered method.The fan blade airfoil is generated by the six profiles described by the non-uniform rational B-spline.The fan blade tendon is parametered by the four parameters.And the fillet section is designed to achieve the smooth transition of the up surface and the bottom surface of the blade root.Based on the requirement of the vibration item of airworthiness,the verification method of vibration compliance for fan blade is introduced.The finite element method（FEM）is carried out to show the compliance of the vibration characteristic and the vibration stress of the fan blade model.The simulation result shows that the vibration characteristic and the vibration stress can meet the requirements of vibration under the entire flight envelope environment,which provides the important reference to the vibration compliance of the fan blade.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2015年第6期884-889,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金委员会与中国民用航空局联合基金(U1333119
60572171
60979019
60939003)资助项目
国防基础科研计划资助项目
中国民用航空局科技(MHRD0722
MHRD200908)资助项目
工信部民机专项(MJF-2011-33)资助项目
关键词
航空发动机
风扇叶片
适航
振动
参数化造型
aeroengine
fan blade
airworthiness
vibration
parametered modeling
