摘要
为有效减小航空发动机静子系统动力特性计算的有限元模型规模,针对压气机静子叶片结构,提出了1种基于截面等效原理的建模简化方法。首先通过1个静子叶片的8、6、4和2截面4种有限元模型的简化和计算说明了该方法的有效性;然后进一步以某型航空发动机压气机的第1级整流器为例,对上述方法进行了计算验证。结果表明：4种简化模型的前5阶固有频率计算结果最大误差分别为2.72%、4.23%、4.73%和7.32%,模态振型吻合良好;简化后的模型规模缩减为原模型的2%～3%,计算时间缩短为原模型的1%~2%。
To reduce the scale of Finite Element （FE） model for the dynamic characteristic calculation of aeroengine stator system, a simplified modeling method for compressor stator vanes was proposed based on the principle of cross section equivalence. Four different simplified FE models of a stator vane, including eight sections, six sections, four sections, and two sections were respectively studied at first to show the validity of the method. Then, taking first stage of compressor straightener of an aeroengine as an example, the effectiveness of the proposed method was demonstrated. The results show that the largest calculation errors of the first 5 natural frequencies of four simplified models are 2.72% ,4.23% ,4.73% and 7.32% respectively, and the mode shapes agree well with those from the original model. With the method, the model scale reduces to 2%-3%, the computing time reduces to only 1%～2% compared with the original model.
出处
《航空发动机》
2015年第6期64-69,共6页
Aeroengine
