基于增材制造的飞机辅助动力端轴流涡轮设计与验证

Design and Verification of Axial Flow Turbine in Aircraft Auxiliary Power End Based on Additive Manufacture

基于有限元分析法研究了增材制造轴流涡轮强度,采用增材制造技术成形了动力端高温轴流涡轮组件并进行超转试验验证。结果表明,增材制造的轴流涡轮变形最大值均出现在叶尖处,涡轮表面最大等效应力值接近GH4251材料的极限屈服强度(830~923 MPa),但仍小于极限抗拉强度(1150~1400 MPa),满足轴流涡轮工作要求。在650℃和涡轮设计转速的115%条件下,涡轮可安全工作5 min,试验后荧光检查及尺寸检查均满足航标要求,证实了增材制造高温合金轴流涡轮技术的可行性。

The strength of additive manufactured axial flow turbine was investigated based on finite element analysis method,and high-temperature axial flow turbine components in power end were formed by additive manufacturing technology,which was verified by overturn test.The results indicate that the maximum deformation values of axial flow turbines by additive manufacturing all appear at the tip of the blade.The maximum equivalent stress value of turbine surface is close to the ultimate yield strength of GH4251 superalloy(830~923 MPa),while far away from the ultimate tensile strength(1150~1400 MPa),which meets the working requirements of axial flow turbines.The turbine can run safely for 5 minutes at 650℃ and 115% of designed rotating speed,and the fluorescence and size inspection meet the requirements of navigation beacon,verifying the feasibility of additive manufacturing of superalloy axial flow turbine.