航空发动机复合材料主轴优化方案设计方法

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%。

Design and optimization method for composite main shaft of aircraft engine

A method was proposed for designing and optimizing composite shaft and a mathematical modal was established based on it. In the model, the quantity was set as objective, and the strength, critical speed and the outer diameter dimensions were set as restraint conditions. The design parameters consist of the thickness of the core, number of composite layers, thickness of single layer and the fiber's direction of each layer. A design and optimization platform was also established by ANSYS for optimizing both the discrete variables and the continuous variables. A low pressure turbine shaft was taken as a design example using metal matrix composite. It can save 36.16% mass compared with the metal one.