本文主要研究航空发动机机匣对断裂叶片的包容性问题。
The article mainly researched into the blade containment in the aeroengine.
用模态实验的方法对某型飞机发动机机匣的模态参数进行了识别。
An engine casing modal experiment and modal parameters extraction have been introduced in the paper.
发动机机匣上安装凸台结构，可简化为机匣壳体开孔后用围壁和加强板组合补强的力学模型。
On engine cases, installation base can be simplified by a mechanics model, which is case shell with hole and a complex of enclosing wall and reinforcing plate for increase strength.
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