某微小涡喷发动机压气机减重设计研究

提高航空发动机的推重比,使发动机最大程度实现轻量化,对微小涡喷发动机压气机的减重设计具有重要意义。对某实心压气机开展有限元计算,得到应力、变形等重要强度考核数据,作为减重优化的设计约束空间。在此基础上,借助等强度结构高强度、高刚度特性,对离心压气机盘的实心部分进行减重优化设计。对比优化前后压气机的承受载荷能力。结果表明:在Mises等效应力小幅增加、叶尖径向位移不显著增加的条件下,压气机减重可达20.3%。

Research on weight reduction design method for compressor of a small turbojet engine

The weight reduction design method of a micro turbojet engine compressor is studied numerically in this paper. Firstly, the finite element calculation is carried out on the solid compressor, and the stress and deformation data of the compressor structure under the condition of the design speed are grasped, which is used as the design constraint space for the weight reduction optimization. On this basis, the weight loss optimization design of the solid part of centrifugal compressor disc is carried out with the help of the characteristics of high strength and high stiffness of honeycomb structure. The results show that the weight loss of the compressor can reach 22% under the condition that the equivalent stress of Mises is not increased and the radial displacement of the tip of the blade is not significantly increased compared with the load bearing capacity of the compressor before and after optimization.