Forming tool for composite fan blade laying layer units

Abstract

The invention discloses a forming tool for composite fan blade laying layer units. The forming tool comprises an overlapping platform (1) and overlapping work surfaces (2) arranged on the overlappingplatform (1); the two sides of the overlapping work surfaces (2) are provided with overlapping reference blocks (3) to serve as an overlapping reference; and the overlapping work surfaces (2) and laying layer units in composite fan blade tenons are the same in quantity. By adopting the forming tool, batch forming of the laying layer units can be achieved in advance, meanwhile, during laying layerunit overlapping, it can be achieved that symmetrical concave and convex units are formed at a time on the same forming mold surface, and the profile quality of the units is improved; then, in the composite fan blade overlapping and laying process, the preformed laying layer units serve as an integrated overlapped layer block to be placed on the blade forming tool; and on the premise that the profile precision of the laying layer units is ensured, the operation time for blade laying layer overlapping can be greatly shortened, and the blade production efficiency is improved.

Description

technical field [0001] The invention relates to a molding tool for a composite material fan blade lamination unit, which belongs to the technical field of composite material manufacturing. Background technique [0002] The fan blade is one of the most representative and important parts of the high thrust-to-weight ratio turbofan engine, and the performance of the turbofan engine is closely related to its development. With the continuous development of high thrust-to-weight ratio engines, the development of fan blades is also deepening. The fan blades have developed from early metal materials to today's carbon fiber resin-based composite materials. Due to the large torsion and double curvature of the composite fan blades themselves The profile, tenon to blade tip thickness changes drastically, and the precision of the part profile is high, making the forming process itself very complicated. Especially for the tenon part of the blade, since the position of the tenon is the ke...

AI Technical Summary

Problems solved by technology

With the continuous development of high thrust-to-weight ratio engines, the development of fan blades is also deepening. The fan blades have developed from early metal materials to today's carbon fiber resin-based composite materials. Due to the large torsion and double curvature of the composite fan blades themselves The characteristics of profile, mortise and blade tip thickness change drastically, and the precision of part profile is high, which makes the forming process itself very complicated.

Especially for the tenon part of the blade, since the position of the tenon is the key position where the blade is connected to the blisk, it bears the largest load, resulting in a complex layer configuration in this area, and there are many layer units. The layer unit is composed of The composition unit of the blade layup is used for filling between the blade tenons. Layers are stacked on the blade forming tooling in sequence. This stacking method has disadvantages such as long stacking cycle and low stacking efficiency, which will lead to higher production costs in the production process of composite fan blades.

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