Layering method for cavity area of composite material blade

The invention belongs to the field of aero-engine blade design and manufacturing, and particularly relates to a composite material blade cavity area layering method which comprises the steps that S1, layering cloth is cut into a plurality of pieces of rectangular layering cloth, each piece of rectangular layering cloth is provided with a first edge and a second edge which are adjacent, and the length of the first edge is equal to that of a cavity area; s2, the first edges of the multiple pieces of rectangular laying cloth are rolled in the direction of the second edges, so that the multiple pieces of rectangular laying cloth are rolled into multiple cylindrical cloth rolls; s3, the two ends of the multiple cylindrical cloth rolls are subjected to beveling and angle shearing; and S4, a plurality of cylindrical cloth rolls are inserted to fill the cavity area, and the defects of the cavity area of the composite stator are reduced. 本申请属于航空发动机叶片设计制造领域，特别涉及一种复合材料叶片空腔区铺层方法，步骤S1：将铺层布裁剪为多个矩形铺层布，所述矩形铺层布具有相邻的第一边与第二边，第一