微小型航空燃气轮机离心叶轮拓扑优化设计

Topology Optimization Design of Centrifugal Impeller for Micro Aviation Gas Turbine

离心叶轮是微小型航空燃气轮机中的关键部件,要求其在满足气动性能的前提下,尽量减轻结构重量,传统设计制造技术已基本发挥到极致,但增材制造技术及拓扑优化设计方法的发展为其进一步优化设计拓展了新的空间。针对某型航空微型燃气轮机离心叶轮减重设计问题,依托增材制造和拓扑优化设计技术,在现有设计的基础上,首先对离心叶轮进行静强度分析,然后开展基于骨架模型的离心叶轮拓扑优化设计及可实现的工艺设计,最后对优化后的模型进行校核。结果表明:该优化设计模型实现离心叶轮减重8.7%,进一步提高了微小型航空燃气轮机的功重比;同时最大变形减少7.5%,最大等效应力减少0.59%,提升了离心叶轮工作时的安全裕度。

Centrifual impeller is a key component in micro aviation gas turbine.It is required to reduce the weight of the structure as much as possible on the premise of satisfying the aerodynamic performance.Traditional design and manufacturing technology is basically played to the extreme,but the development of additive manufacturing technology and topology optimization design method has expanded new space for its further optimization design.Aiming at the weight reduction design problem of a certain type of aviation micro gas turbine centrifugal impeller,relying on additive manufacturing and topology optimization design technology,based on the existing design,the static strength analysis of the centrifugal impeller is carried out first,and then the centrifugal impeller topology optimization based on the skeleton model and achievable process design is developed.Finally the optimized model is checked.The results show that the optimized design model can reduce the weight of the centrifugal impeller by8.7%,and the power-gain ratio of the micro-gas turbine can be further improved,the maximum deformation is reduced by 7.5%.The maximum equivalent stress is reduced by 0.59%,which improves the safety margin of centrifugal impeller when working.