Molding device and method of torsional thickness-variable composite structure

Abstract

The invention belongs to molding technologies of preforms of resin matrix composites, and particularly relates to a molding device and method of a torsional thickness-variable composite structure. Dueto the lack of processing precision of the preforms and the limitation on the knitting technology, difference exists between the thickness of knitted blade preforms and theoretical thickness of the blades, and the phenomenon that the preforms and molded surfaces conduct secondary fitting and compacting exists in the mold closing process. The molding device of the torsional thickness-variable composite structure comprises a base, transverse pressing blocks and longitudinal pressing blocks, wherein the upper surface of the base coincides with the lower surfaces of twisted preforms, the lower surfaces of the transverse pressing blocks and longitudinal pressing blocks coincide with the upper surfaces of the twisted preforms, precise deformation control over the thickness-variable blade preforms from the planar state to the twisted state is achieved, the deformation precision is significantly improved, and the deformation process is controllable. The problem of local extruding or slippingdeformation caused by simultaneous compression of preforms in different thickness areas is avoided.

Description

technical field [0001] The invention belongs to the resin-based composite material prefabricated body molding technology, and in particular relates to a molding device and method for a torsion-variable-thickness composite material structure. Background technique [0002] Carbon fiber reinforced resin-based composite materials 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. The amount of key materials used in equipment has also become one of the symbols of the advanced nature of aviation equipment. Composite material blades are widely used in aero-engines with high-precision composite parts. Composite material blades directly affect the aerodynamic performance and noise indicators of the engine. The aerodynamic force caused by the vibration of the blade, the fatigue load caused by the vibration of the blade, and the impact of foreign objec...

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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