The invention discloses a
composite material fan blade layering design method in the technical field of aero-engine
fan blade design, and the method comprises the following steps: S1, constructing a blade model, and carrying out optimization based on a model structure; s2, prepreg is selected, the curing thickness of a single layer of prepreg is obtained through a laminated plate curing process, a laying layer
profile diagram is extracted according to the blade optimization model, and laying
layers are grouped according to the height; s3, paving
layers are uniformly arranged according to a height
marshalling method under the paving layer design criterion condition, paving layer angles are given, whether the requirements are met or not is judged, and a preliminary blanking drawing is generated; and S4, carrying out
cutting design on the prepreg according to the blanking drawing. According to the method, through parametric modeling and actual measurement
data calibration, tenon extension design and layering angle distribution and sorting design are optimized,
fiber continuity is ensured, process accumulative errors are eliminated, then, 90-degree layering is locally introduced to enhance out-of-plane rigidity,
stress concentration is dispersed in combination with step transition treatment, and therefore the method has the advantages of being simple in structure and convenient to operate. And the
peak value of the interlayer
shear stress of a tenon-blade body transition area is reduced, and the
impact resistance is improved.