航空发动机风扇叶片冲击加强轻量化设计

Lightweight Design for Improving Aeroengine Fan Blade Impact Resistance Capability

以提高风扇叶片抗冲击性能为目标,以空心率为约束条件,进行风扇叶片创新构型设计优化,并通过试验件加工和性能评估,验证所设计方案的合理性.建立了瞬态冲击载荷静力学等效方法,获取了风扇叶片在工作状态下能够有效抵抗鸟撞冲击载荷的最优质量分布.基于优化结果,建立了低质量、高抗冲击性能的风扇叶片几何构型.通过3D打印风扇叶片优化构型试验件,进行加工工艺可行性和优化构型试验件的力学性能评估,验证了优化设计方案的工艺可实现性、静力性能和抗鸟撞性能.结果表明:上述优化方法的建立能够为航空发动机空心风扇叶片设计提供可行的技术手段,使得叶片空心率提高到45%以上,并显著提升叶片抗冲击性能.

In order to improve the impact resistance of fan blades,this paper optimizes the innov ative configuration design of fan blades with the constraint of the hollow ratio.The feasibility rationality of the optimized solution was verified through the processing of test pieces and performance evaluation.T he static equivalent method of transient impact load was established to obtain the opt imal mass distribution of the fan blade that can effectively resist bird impact load under working conditions.Based on the optimization results,the fan blade topology optimization was reconstructed,and the geometric configuration of fan blade with low mass and high impact resistance was established.Based on 3D printed fan blade to optimize the configuration test sample,the feasibility of the processing technology and the mechanical properties of the optimized configuration of fan blades were evaluated by 3D printing.The process reliability,static force and bird impact resistance of the optimized design were verified.The res ults show that the proposed optimiza tion method can be used for the design of hollow fan blades of aero enginewith a hollow ratio of over 45%,and the impact resistance of the blades is significantly improved.