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提出了航空发动机复合材料主轴优化设计方法,建立了以质量最轻为目标函数,以强度、临界转速和外径尺寸为约束,以轴芯厚度、复合材料层数、各层厚度和各层铺设角度为优化设计变量的优化数学模型。基于ANSYS软件,建立了发动机复合材料主轴优化方案设计平台,着重解决了可同时进行离散和连续设计变量优化的问题。以低压涡轮主轴为例,进行了金属基复合材料主轴优化设计,设计的复合材料主轴质量比同负荷金属轴减少36.16%。
Aiming at the optimization of aeroengine composite material spindle, aiming at the lightest mass as the objective function, the strength, critical speed and outer diameter are taken as constraints, the thickness of the core, the number of composite layers, the thickness of each layer and the laying of each layer Optimum mathematical model for optimizing design variables. Based on the ANSYS software, a design platform of engine composite spindle optimization scheme is established, which solves the problem that both discrete and continuous design variables can be optimized simultaneously. Taking the low-pressure turbine main shaft as an example, the optimal design of the metal matrix composite spindle is carried out. The quality of the composite spindle is reduced by 36.16% compared with that of the same load metal shaft.