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为了分析航空发动机叶片-机匣碰摩摩擦热对叶片的影响,基于有限元法建立了叶片-机匣碰摩摩擦的热-结构直接耦合模型,分析了不同偏心距和转速对模型应力场和温度场的影响,并与未考虑摩擦热效应的碰摩模型进行对比。结果表明:当叶片与机匣之间发生摩擦时,需考虑材料参数随温度变化的影响;摩擦热主要分布在接触表面较小的区域,温度分布沿接触面向四周呈递减趋势,且温度梯度越来越小。并在该区域产生了较大的热应力;随着偏心距和转速的增大,叶片-机匣的摩擦热效应越发明显。在实际工程问题中,需考虑摩擦热效应对叶尖表面损伤的影响。
In order to analyze the influence of frictional heat of blade-rotor on aeroengine blades, a thermo-structural direct coupling model of blade-case frictional friction is established based on the finite element method. The effects of different eccentricity and rotation speed on the model stress field and Temperature field and compared with the rub-impact model without considering the frictional heat effect. The results show that when the friction between blade and casing occurs, the influence of temperature on the material parameters should be considered. The frictional heat mainly distributes in the area with smaller contact surface, and the temperature distribution decreases gradually along the contact surface, and the temperature gradient The smaller it is. And produced large thermal stress in this area. With the increase of eccentricity and rotation speed, the frictional heat effect of blade-casing becomes more obvious. In practical engineering problems, the influence of frictional heat effect on the tip surface damage needs to be considered.