Manufacturing method for aeroengine fan blades

Abstract

The present disclosure provides a manufacturing method for an aeroengine fan blade, comprising: step A: processing the shape of the hollow metal skeleton; step B: performing fiber weaving or seaming on the hollow metal skeleton to obtain a composite solidified core; step C: Lay the prepreg layer on the surface of the composite curing core, adjust the leaf shape and size of the blade; Step D: Use the interlayer reinforcement method to strengthen the interlayer of the prepreg layer and the prepreg layer and composite curing Strengthening the bonding between the cores; step E: performing secondary curing with an autoclave to form the outer shell of the blade. The composite material fan blade produced by the disclosure is light in weight, can withstand the impact of bird strike, has a stronger structure, and is less prone to interlayer separation, and meets the stringent requirements of aeroengine fan blade composite materials.

Description

technical field [0001] The present disclosure relates to the field of aeroengine fans, in particular to a manufacturing method for aeroengine fan blades. Background technique [0002] Resin-based composite wide-chord fan blades not only have advanced aerodynamic performance and anti-vibration ability, but also can significantly reduce structural weight and have high propulsion efficiency. They are more and more widely used in the development and use of engines. The design and technology of the existing large bypass ratio fan blades in China are not mature, and there are deficiencies such as poor bird strike resistance and easy delamination and cracking. The tape-laid fan blades manufactured based on the traditional process method cannot meet the impact requirements, and are prone to delamination; in addition, the root strength of the blade manufactured by the integral weaving process method is insufficient, and the root is prone to breakage. [0003] In the prior art, the o...

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Problems solved by technology

[0005] In the prior art, it is also provided that the blades are all printed by additive manufacturing, and the blades are all metal materials manufactured by additive manufacturing on the blade surface, and the use of resin-based composite materials as the final blade forming material is not considered. Superficially designed and manufactured weight-reducing structure, may not achieve optimal weight-reducing effect

Another hybrid turbine blade and process including a plurality of insert sections, the fan blade is formed by laying up different materials along the thickness direction in at least one chordwise section, and the layers are solidified by bonding, the The strength of this process forming method may not be as good as using the intermediate metal skeleton as the only force-bearing and force-transmitting unit to resist flying birds, etc., and the processing difficulty may be higher, and the overall process method may be more complicated

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