The invention belongs to the field of aero-engine structural design and strength analysis, and relates to a
composite material closed annular casing layering design structure which comprises a
barrel, a transition area, a thickening area, an R area and a
flanging which are sequentially connected, the
barrel, the transition area, the thickening area, the R area and the
flanging are all integrally arranged, that is, continuous layering is generally carried out on a casing from the
barrel to the
flanging, and the thickness of the casing is larger than that of the barrel. A
metal mounting edge and a
rivet connecting structure thereof are omitted, so that the load transmission efficiency of the
cartridge receiver is improved; the problem that
thermal deformation of different materials in the casing in the working state is not coordinated is solved; the
layer thickness of the turnup is the same as that of the thickening area, the layer between the thickening area and the transition area is gradually decreased from the thickening area to the transition area in a stepped mode, and the layer between the transition area and the barrel is gradually decreased from the transition area to the barrel in a stepped mode, so that the thickened layer state extends to the
cartridge receiver barrel. According to the layering design method, the weight reduction design requirement of engine parts is considered while the strength requirement of each part of the case is ensured, and the number of layering
layers is minimized.