Forming method for composite blade of aircraft engine

A technology of aero-engines and composite materials, applied in the direction of coating, etc., can solve the problems of the inevitable reduction of fiber performance and the inability to further increase the proportion of axial fibers, etc., achieve high bypass ratio, improve integrity and impact resistance, and large interface The effect of binding strength

Active Publication Date: 2017-06-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

Three-dimensional weaving technology cannot further increase the proportion of its axial fibers, and in three-dimensional weaving, it is inevitable that the performance of the fibers will be reduced at the nodes, which is prone to damage

Method used

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  • Forming method for composite blade of aircraft engine
  • Forming method for composite blade of aircraft engine

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Embodiment Construction

[0025] The following is based on figure 1 with figure 2 The specific embodiment of the present invention is further described:

[0026] see figure 1 with figure 2 , a molding method of a composite material blade of an aero-engine, comprising the following steps:

[0027] (1) unfolding the carbon fiber tow, impregnating the unfolded carbon fiber tow with thermoplastic resin slurry 4 to obtain an intermediate tow 9;

[0028] (2) drying the intermediate tow 9;

[0029] (3) The intermediate tow 9 is heated by means of ultrasonic vibration heating, and the heated intermediate tow 9 is laid layer by layer by a dry laying method, and the blade prefabricated body 13 is formed after laying;

[0030] (4) Put a carbon fiber fabric cover 14 on the outside of the blade prefabricated body 13, and use a three-dimensional sewing method to stitch the edges of the carbon fiber fabric cover 14 and the internal blade prefabricated body 13;

[0031] (5) Put the stitched blade preform 13 an...

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Abstract

The invention discloses a forming method for a composite blade of an aircraft engine. The forming method includes the following steps that carbon fiber bundles are unfolded, the unfolded carbon fiber bundles are soaked with thermoplastic resin slurry, and intermediate bundles are obtained; the intermediate bundles are dried; the intermediate bundles are heated in an ultrasonic vibration heating mode, the heated intermediate bundles are laid layer by layer in a dry laying mode, and a blade preform is formed after laying; the blade preform is sleeved with a carbon fiber fabric sleeve, and the carbon fiber fabric sleeve and the internal blade preform are subjected to edge sewing through a three-dimensional sewing method; and the sewn blade preform and carbon fiber fabric sleeve are put into an RTM mold and are subjected to mold closing and curing molding through the RTM technology, and the composite blade is obtained. According to the forming method, the proportion and accurate positioning of axial fibers are guaranteed, and thus the integrality and impact resistance of the composite blade are improved.

Description

technical field [0001] The invention belongs to the field of automatic molding of composite materials, and in particular relates to a molding method of composite material blades of an aero-engine. Background technique [0002] Resin-based composite materials have low high temperature resistance, but they have light weight, high specific strength and specific modulus, good fatigue resistance and corrosion resistance, good damping characteristics, strong designability and mature molding process, and have been used in aero-engines. The cold-end components (mainly including the external casing of the engine, the stator blades, the containing casing of the rotor blades, the engine nacelle, the thrust reverser and other components) have been widely used, which can significantly reduce the weight of the engine, reduce the development cost of the engine, and greatly improved engine performance. [0003] After decades of development, the manufacturing process of the fourth-generatio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/48B29C70/54B29C70/30B29B15/14B29B15/08B29B13/02
Inventor 还大军李勇褚奇奕肖军齐俊伟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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