Composite material closed annular casing layering design structure

Abstract

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.

Description

technical field [0001] The application belongs to the field of aero-engine structure design and strength analysis, and particularly relates to a composite material closed annular casing layup design structure. Background technique [0002] Composite materials have been used in aerospace product design due to their light weight, excellent material properties, and strong designability. Due to limitations in the installation, use, and maintenance requirements of aero-engine components, as well as the molding technology and processing methods of composite materials, only some casings can be made of composite materials. Therefore, in the design of aero-engine casing, not only the structural design of the casing is required, but also the connection design between the composite material casing and other metal casings. The connection structure is characterized by large load transfer, complex load form, Withstand high temperature environments. [0003] The engine case mainly bears ...

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Problems solved by technology

[0012] The purpose of this application is to provide a laminate design structure of a composite material closed ring casing to solve the problems caused by the use of rivets to connect the metal mounting edge of the composite material casing in the prior art. The problem of poor carrying capacity of the receiver

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