Laminate Design And Anslysis Of Composite Fan Blade Doetail

Carbon fiber composite has the advantages of low density,high specific strength,high specific stiffness,strong design ability,and good fatigue fracture resistance.Resin-based carbon fiber composite is increasingly used in large ducted turbofan engine blade.The fan blade dovetail is the part with the largest number of layers and a decreasing concentration of the layer.The laminate design is difficult.The research goal of this article focuses on the dovetail of composite fan blade.According to the structural of the dovetail,the laminate design of dovetail is completed.The layers are divided into structural layer and insert layer.The structural of a single group of insert layers is studied.The number of single group insert layers,the internal layer sequence,the layer angle,the slope formed by the insert layers,and the staggered distance between adjacent groups of insert layers,a method suitable for the laminate design of fan blade dovetail has been established.Based on the Fiber SIM-ACP software platform,the finite element modeling of the dovetail was conducted,and the influence of the element size on the quality of FEM of dovetail and the calculation results of inter-laminar stress were studied.A finite element model of the dovetail that met the accuracy requirements of the interlayer stress analysis was determined.By comparison with the experimental results,the validity of the finite element model is confirmed.According to the laminate design plan,the dovetail is autoclaved.By increasing the molding process and the number of pre-curing process to optimize the molding process.The forming quality of the dovetail is improved,and the thickness deviation is less than±0.7mm.Static tensile test and high-cycle fatigue test were performed on the formed dovetail specimens.The ultimate load,failure mode,and cracks appear position of the dovetail were determined by tensile test.The resonance residency method was used to test the high-cycle fatigue characteristics of the dovetail in the first-order bending mode.The fatigue life of the dovetail under the 2473??strain level is 1.11?10~6.The research in this article explores a set of iterative systems suitable for aero-engine composite fan blade laminate design,finite element analysis,manufacturing and test verification.