Manufacturing method of aero-engine composite material fan blade metal stiffened edge

Abstract

The invention relates to a manufacturing method of an aero-engine composite material fan blade metal stiffened edge. The manufacturing method of the aero-engine composite material fan blade metal stiffened edge mainly comprises the steps that diffusion bonding is carried out on a prefabricated piece through a sealing structure to obtain a hollow structure, and finally, the metal stiffened edge isisolated in an edge trimming separation mode. A core model is adopted to support a cavity in the process of diffusion bonding, and the forming precision and quality of the inner cavity surface of themetal stiffened edge are ensured. Compared with the prior art, the problems of low material utilization, difficult machining and long production period caused by integral cutting machining of the metal stiffened edge are solved, and the defects of nonuniform thickness distribution and low forming precision of an inner cavity small circular bead caused by a superplastic forming/diffusion bonding method are overcome.

Description

technical field [0001] The invention relates to a method for manufacturing a reinforced edge of a thin-walled deep cavity, in particular to a method for manufacturing a metal reinforced edge of an aero-engine composite fan blade. Background technique [0002] Fan blades are one of the most important components of modern commercial aircraft engines, accounting for about 30% to 35% of the total mass of the engine. Reducing the mass of the fan section is a key means to reduce the mass of the engine and improve the efficiency of the engine, and the use of composite material fan blades is the only way to achieve a higher bypass ratio and weight reduction of the engine. Compared with titanium alloy hollow blades, composite fan blades have the advantages of light weight, high efficiency, and low noise, and the number of composite blades is less, with better anti-flutter performance and damage tolerance capabilities, and anti-bird strike performance It can also meet airworthiness r...

AI Technical Summary

Problems solved by technology

However, the impact resistance, compression resistance and lightning strike resistance of composite materials are worse than those of metal, especially at the leading edge of the blade, so the use of titanium alloy for edge wrapping is a commonly used method

[0003] The reinforced edge of the leading edge of the composite fan blade has the characteristics of complex, narrow, deep cavity, special-shaped and thin-walled, and the full-cut long-cycle processing method is adopted, and the material utilization rate is very low.

Due to the thin, narrow and deep wall of the cavity structure, it has high requirements on the cutting tool, the tool is prone to instability, the processing cycle is long, waste products are prone to occur, the processing cost is high, and it is not suitable for commercial application. Therefore, diffusion bonding and cutting processing are used. Combined manufacturing methods will be an inevitable trend of development

[0004] After searching the prior art, it was found that Chinese Patent Application No. 200510053532.2, published on July 27, 2005, discloses a method for manufacturing reinforcement components for the front or rear of fan blades, which involves processing by superplastic forming / diffusion bonding Non-hollow parts are processed by cutting two thick plates, diffusion bonding, superplastic forming and cutting. This process uses superplastic forming to form the inner cavity. However, the thickness will be significantly thinner during the forming process, and the thickness distribution will be different. Uniform, small fillet accuracy of superplastic forming can not meet the design requirements

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