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通过对航空发动机的叶冠的功能及设计原理进行分析,总结出其中的不利影响,从而有针对性地进行叶冠造型优化,一方面通过减轻叶冠局部质量来降低叶片负荷,另一方面通过增加封严篦齿增加叶冠的接触面积。再通过建立叶片三维分析模型,分析优化前后叶冠的力学性能、接触状态等。结果表明:合理地减轻局部质量,可以有效降低叶冠局部的最大应力,改变叶冠与叶身相交倒圆R处的最大应力位置,避免在铸造薄弱区域出现应力集中;通过增加封严篦齿,降低叶冠接触面的应力水平,从而减轻磨损,提高叶片的可靠性。
Through the analysis of the function and design principle of the aero-engine blade crown, the adverse effects are summed up so as to optimize the blade crown design. On the one hand, the blade load can be reduced by reducing the local mass of the blade crown. On the other hand, Increasing the seal labyrinth increases the contact area of the leaf crown. Then through the establishment of three-dimensional analysis of leaf model, analysis of the mechanical properties of the crown before and after optimization, contact status. The results show that the local stress can be effectively reduced by reducing the local mass, and the maximum stress position at the intersection R of the blade and the blade can be changed to avoid the stress concentration in the weak area of the casting. , Reduce the stress level at the contact surface of the crown to reduce the wear and improve the reliability of the blade.