论文部分内容阅读
鸟撞击是飞行安全最严重的威胁之一。鸟撞击的后果非常危险,因而,在进入服役之前,飞机部件必须通过抗鸟撞认证。航空发动机风扇转子叶片是容易受到飞鸟撞击的飞机部件之一,在设计时必须考虑使航空发动机风扇转子叶片具有抗鸟撞击的能力,降低由于鸟撞击叶片而引起的飞行事故。采用接触冲击算法,对航空发动机风扇转子叶片进行了模拟鸟撞击数值仿真。针对风扇叶片具有阻尼凸台的特点,分析中建立了三叶片组计算模型。得到了对应试验测试点的模拟鸟撞击叶片的瞬态响应曲线、叶片的位移和当量应力。比较了试验中和数值仿真中模拟鸟撞击叶片的瞬态响应曲线,试验中测试点与数值仿真中对应点的变化基本相同。分析了叶片的变形过程、最大位移和最大当量应力。模拟鸟撞击风扇叶片数值仿真验证并补充了模拟鸟撞击风扇叶片试验结果。
Bird strike is one of the most serious threats to flight safety. The consequences of a bird strike are very dangerous, and therefore aircraft components must pass bird strike certification before entering service. Aero-Engine Fan Rotor blades are one of the aircraft components that are susceptible to impact by a bird and must be engineered to take into account the ability of the aero-engine fan rotor blade to resist bird impact and reduce flight accidents due to bird impact on the blade. The contact impact algorithm is used to simulate the impact of aero-engine rotor blades on a simulated bird strike. In view of the characteristics of fan blades with damping bosses, a three-blade calculation model was established in the analysis. The transient response curve of the simulated bird impact blade corresponding to the experimental test point, the displacement of the blade and the equivalent stress were obtained. The transient response curves of simulated bird impact blades in the experiment and numerical simulation are compared. The changes of the corresponding points in the test points and the numerical simulation are basically the same. The deformation process, the maximum displacement and the maximum equivalent stress of the blade were analyzed. Numerical simulations of simulated bird strike fan blades were performed to verify and supplement the simulated bird strike fan blade test results.