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根据涡轮冷却叶片热-固耦合分析和基于遗传算法-有限元的涡轮叶片优化设计方法,发展了涡轮冷却叶片热-固一体化优化设计方法.以某航空发动机涡轮转子叶片为原型,分析了冷却孔的位置、形状(圆形和四边形)、大小和数量对热应力与冷却效果的影响.结果表明,该方法能有效地降低涡轮叶片的应力、改善其冷却效果;四边形孔具有更好的冷却效果和更低的最大应力;随着冷却孔大小和数量的增加,最高温度下降,而最大应力上升.
According to the thermo-mechanical coupling analysis of turbine cooling blade and the optimization design method of turbine blade based on genetic algorithm-finite element method, the optimization design method of thermo-solid integration for turbine cooling blade is developed. Taking aeroengine turbine rotor blade as the prototype, The results show that this method can effectively reduce the stress of turbine blades and improve the cooling effect. The quadrilateral holes have better cooling performance Effect and lower maximum stress; as the size and number of cooling holes increases, the maximum temperature decreases and the maximum stress increases.