Aero-engine fan blade and manufacturing method thereof

Abstract

The invention provides an aero-engine fan blade and a manufacturing method of the aero-engine fan blade. The manufacturing method of the aero-engine fan blade comprises the following steps of S1, machining a metal framework, wherein the cross section of the metal framework is of a single-arrow or double-arrow perforated arc structure; S2, arranging brazing filler metal on the surface of the non-arrow portion of the metal framework; S3, winding fibers on the surface of the metal framework through holes in the metal framework so as to enable the fibers to form a fiber woven body; S4, heating thebrazing filler metal so as to enable the brazing filler metal to be melted and infiltrated into some portions of the fiber woven body; and S5, infiltrating resin into the portions, with no infiltrated brazing filler metal, of the fiber woven body and curing the resin to form the aero-engine fan blade. The aero-engine fan blade comprises the metal framework (100) and a curing layer (200), whereinthe curing layer (200) comprises a brazing filler metal fiber curing layer (201) and a fiber resin curing layer (202). By means of composite weaving and brazing, blades of the aero-engine fan are lower in weight and higher in strength.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to an aero-engine fan blade and a manufacturing method thereof. Background technique [0002] With the continuous improvement of the thrust-to-weight ratio requirements of aero-engines, composite materials are used more and more frequently, and composite materials have the characteristics of anisotropy. If they are in the same direction as the blades, they can withstand extremely large loads Its light weight can effectively reduce the weight of the blades and even the entire engine. However, the fan blades of the engine are getting longer and longer. The blades of the tape laying method cannot meet the impact. The edge is weakly rigid in space, difficult to process, and high in cost; small blades have small structural size and thin blades, and the weight reduction effect of traditional designs is not obvious, and the structural strength decreases, which is not conducive to the ...

AI Technical Summary

Problems solved by technology

[0002] With the continuous improvement of the thrust-to-weight ratio requirements of aero-engines, composite materials are used more and more frequently, and composite materials have the characteristics of anisotropy. If they are in the same direction as the blades, they can withstand extremely large loads Its light weight can effectively reduce the weight of the blades and even the entire engine. However, the fan blades of the engine are getting longer and longer. The blades of the tape laying method cannot meet the impact. The edge is weakly rigid in space, difficult to process, and high in cost; small blades have small structural size and thin blades, and the weight reduction effect of traditional designs is not obvious, and the structural strength decreases, which is not conducive to the use of composite materials on engines with small bypass ratios and high speeds usage of

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