航空发动机风扇叶片的抗鸟撞设计

根据航空发动机结构特征和鸟撞后的风扇叶片损伤特征,提出风扇第一级转子叶片是发动机抗鸟撞关键零件,叶片前缘为抗鸟撞设计关键部位。建立一种风扇叶片鸟撞理论分析方法,研究撞击工况、结构参数与鸟撞过程、损伤模式、损伤程度的关系,提出前缘角度是抗鸟撞能力关键结构参数。当撞击工况确定后,前缘角度决定了撞击形式和叶片损伤模式,影响损伤程度。采用显示动力学仿真分析方法,设计了一种带前缘特征的模型,对前缘角度的影响规律进行了验证,并开展了实际风扇叶片改进设计,改进后的叶片被鸟撞击后变形减小最少33%,抗鸟撞击能力明显提升。

Design for anti-bird impact of aero-engine fan blade

The first stage fan rotor blade is a key component of the engine against bird impact, and the leading edge of the blade is a key part of the anti-bird impact design, by investigating the structural characteristics of the engine and the damage characteristics after bird impact. Therefore, a theoretical analysis method of fan blade bird impact was established to study the relationship among impact conditions, structural parameters and bird impact process, and damage mode as well as damage degree. Results show that the leading edge angle is the key structural parameter of anti-bird impact. The leading edge angle determined the impact process, damage mode and damage degree, when the bird impact conditions were determined. A model with leading edge characteristics was designed and the influence rule of leading edge angle was verified using the method of display dynamics simulation analysis. Based on the results, an improved design of the actual fan blade was carried out. The deformation of improved blade was reduced by a minimum of 33% after being hit by a bird, and the anti-bird impact ability of the improved blade was obviously improved.