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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。
Aero-engine fan blade vibration airworthiness compliance design methods were studied. The non-uniform rational B-spline is adopted to realize the design of the fan blade profile, the fan blades are overlapped and formed by the cross-section profile centroids, the sketch of the tenon is established, the arc tenon is generated to generate the fan blades, and the strength and vibration characteristics are realized The root of the design section. Based on the requirement of Vibration Airworthiness Clause CCAR 33.83, the verification method of fan blade vibration compliance is given. Based on the established fan blade model, the vibration characteristics and vibration stress of fan blade are calculated by finite element method. The calculation results show that the vibration characteristics and vibration stress of the fan blade meet the airworthiness requirements of the vibration throughout the flight envelope environment and provide the basis for the design and verification of the vibration compliance of the fan blade.