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基于适用于纤维增强复合材料的细观力学代表体积元(RVE)法和材料强度失效参数计算公式,计算体积分数为40%的SCS-ULTRA纤维增强TC17基复合材料的力学性能参数和强度失效参数,建立以实际某型号发动机低压涡轮轴为背景,并用SCS-ULTRA纤维增强TC17基复合材料代替原有高温合金材料,应用复合材料宏观强度准则中的蔡—吴张量失效准则,对其进行静强度计算与失效判定,总结作为衡量趋近失效程度的蔡—吴强度指数随轴结构复合材料铺层数的变化规律,同时对铺层总数为27层的轴结构进行给定载荷下的强度计算,得出轴结构内部每一铺层的强度指数及铺层强度指数随铺层位置、45°铺角不同的变化规律,并预测在极限载荷下轴结构铺层首先出现失效的情况。
The mechanical properties and strength failure parameters of SCS-ULTRA fiber reinforced TC17 matrix composites with a volume fraction of 40% were calculated based on the RVE method and the material strength failure parameter calculation formula applicable to the fiber reinforced composites , The paper established the low-pressure turbine shaft of a certain type of engine as the background and replaced the original superalloy material with SCS-ULTRA fiber reinforced TC17 matrix composite material. The static strength of the composite material was calculated by applying the Ts-Wu tensor failure criterion in macroscopic strength criterion And failure judgment, we summarize the variation law of CAI-Wu strength index with the number of layers of composite materials of axial structure, and calculate the strength under axial loads with a total load of 27 stories The strength index and lay-up strength index of each ply inside out-axis structure vary with lay position and 45 ° lay angle, and predict the first failure of the shaft layup under the limit load.