Forming device and method for twisted variable-thickness composite material structure

Abstract

The invention belongs to a forming technology for a resin matrix composite material preform, and specifically relates to a forming device and method for a twisted variable-thickness composite materialstructure. Due to insufficient machining accuracy for a preform and a limit of a weaving process, a difference exists between the thickness of the weaved preform of a blade and a theoretical thickness of the blade, and the phenomena of secondary bonding and compaction with a molded surface, of the preform, exist in a die assembly process. The forming device for the twisted variable-thickness composite material structure comprises a base, a transversal press block and a longitudinal block, wherein the upper surface of the base is the same as the lower surface of the twisted preform, the combined lower surface of the transversal press block and the longitudinal block is the same as the upper surface of the twisted preform, and accurate deformation control over the variable-thickness preformof the blade from a planar state to a twisted state is realized, so that the deformation accuracy is remarkably increased, and the deformation process is controllable; and the problem of local extrusion or slide deformation which is brought by simultaneous compression of preforms in areas with different thicknesses, is avoided.

Description

Technical field [0001] The invention belongs to the molding technology of a resin-based composite material preform, and in particular relates to a molding device and method for a twisted variable thickness composite material structure. Background technique [0002] Carbon fiber reinforced resin matrix composites have unique advantages such as light weight, high specific strength, high specific modulus, good fatigue fracture resistance, corrosion resistance, and easy large-area integral forming. They have been widely used in aviation aircraft and engine structures and become aerospace The amount of key materials for equipment has also become one of the signs of advanced aviation equipment. Composite material blade is a kind of composite material with high precision requirements widely used in aeroengines. Composite material blades directly affect the aerodynamic performance and noise index of the engine, and also need to withstand the huge centrifugal force generated by high-speed...

AI Technical Summary

Problems solved by technology

Among them, the positioning method of the preform in the mold has been disclosed by the patent CN201711345855.8. However, due to the structural complexity of the composite fan blade, even if the preform and the mold are positioned before the mold is closed, due to the processing of the preform Insufficient precision, the prefabricated body and the mold surface cannot be completely fitted in place; at the same time, due to the limitation of the weaving process, the thickness of the blade weaving prefabricated body is different from the theoretical thickness of the blade, which is usually thicker than the theoretical thickness. During the process, there is a phenomenon of secondary bonding and compaction of the prefabricated body and the profile

Therefore, during the mold closing process, the secondary bonding between the preform and the smooth mold surface and the structural deformation caused by the local compaction of the preform will cause the preform to slip during the mold closing process, resulting in post-molding The position of the weaving structure of the blade does not match the theoretical position, resulting in the scrapping of parts

In addition, due to the complexity of the blade structure, there are different partitions in the internal structure of the braided blade, and some structures have fewer interweaving points and the structural stability is not good enough, which leads to the erosion deformation caused by the pressure during resin injection, resulting in the structural deformation of the blade after molding Phenomenon, resulting in scrapped parts

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