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Continuous fiber reinforced composite propeller layer lay-up design and preparation method

A reinforced composite material and continuous fiber technology, applied in the field of materials, can solve the problems of high price and low production efficiency, and achieve the effect of improving production efficiency, improving product quality and ensuring continuity

Active Publication Date: 2018-01-19
725TH RES INST OF CHINA SHIPBUILDING INDAL CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The integrally formed continuous fiber propeller requires three-dimensional weaving of the preform, which is realized through the RTM process, which is expensive and has low production efficiency

Method used

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  • Continuous fiber reinforced composite propeller layer lay-up design and preparation method
  • Continuous fiber reinforced composite propeller layer lay-up design and preparation method
  • Continuous fiber reinforced composite propeller layer lay-up design and preparation method

Examples

Experimental program
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preparation example Construction

[0044] The blade 8 of the present invention is formed by stacking continuous fiber prepreg sheets, such as Figure 4 As shown, the hub 1 is composed of a metal insert 6 and multiple layers of continuous fiber prepreg sheets wound outside the metal insert 6 . A continuous fiber reinforced composite propeller layup design and preparation method, comprising the following steps:

[0045] Step 1. Blade geometry processing and blade shape design

[0046] (1) Geometric processing of blades:

[0047] Extract the geometric mid-plane 2 of the propeller as the reference surface for propeller design; define the part of the blade 8 above the geometric mid-plane 2 as the upper half 3 of the blade, and define the part of the blade 8 below the geometric mid-plane 2 as the lower half of the blade Section 4, as in figure 1 As shown; the part of the propeller hub located between two adjacent blades 8 and outside the reference curved surface (geometric midplane 2) is defined as a continuous ar...

Embodiment 1

[0068] A continuous fiber reinforced composite propeller layup design and preparation method, comprising the following steps:

[0069] Take a geometrical longitudinal section of the propeller along a plane passing through the midline of the three-blade propeller blades (eg Figure 5 As shown), the thickness of the blade near the hub is 26.67mm, the thickness of the blade near the outer edge is 6.72mm, and the radius of the propeller blade is 200mm.

[0070] Extract the middle surface layer by 3D design software, extract the middle surfaces of two adjacent blades for rotation, and perform Boolean operations with the propeller to obtain a 3D map of the preformed blade, as shown in figure 1 shown.

[0071]The measured area with the largest thickness of the preformed blade is a continuous area, which is about 18.24 mm. The unidirectional fiber prepreg is selected, the reinforced phase is T700 unidirectional carbon fiber, the resin is tough epoxy resin, and the average thickness ...

Embodiment 2

[0079] A continuous fiber reinforced composite propeller layup design and preparation method, comprising the following steps:

[0080] The propeller is geometrically longitudinally sectioned along the plane passing through the midline of the three-bladed propeller blades. The thickness of the blade near the hub is 64.73mm, the thickness of the blade near the edge is 22.6mm, and the radius of the propeller blade is 400mm.

[0081] The mid-surface layer is extracted by 3D design software, and the mid-surfaces of two adjacent blades are extracted for rotation, and Boolean operations are performed with the propeller to obtain a 3D map of the preformed blade.

[0082] The region with the largest thickness of the preformed blade is the blade root region, with a thickness of 32.37mm, and the thickness of the continuous region is 28.44mm. The unidirectional fiber prepreg is selected as the reinforced phase of T700 carbon fiber fabric, and the resin is tough epoxy resin with an average...

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Abstract

The invention provides a continuous fiber reinforced composite propeller layer lay-up design and a preparation method. According to the method, continuous fiber prepreg sheets are adopted for coatinga metal insert; through the mold pressing process, the one-step forming of a composite propeller is achieved; a preformed mold is prepared for the preforming process of composite blades, thereby guaranteeing the continuity of the connection between the blades and a propeller hub, shortening the manufacturing cycle of the composite propeller, reducing the manufacturing cost of the composite propeller, improving the product quality, and meeting the actual usage requirements on the light weight of a propeller blade material and the noise reduction; according to the propeller prepared through themethod, the continuous fiber integral blades are adopted and integrally connected with the propeller hub part, thereby avoiding the occurrence of a secondary interface; and accordingly, the machinerystability and reliability can be effectively improved.

Description

technical field [0001] The invention relates to the field of material technology, in particular to a continuous fiber reinforced composite material propeller layer design and preparation method. Background technique [0002] Existing composite propellers generally have a combined structure, that is, blades and hubs are prepared separately, then assembled by tenon joints or plug joints, and secondary treatment is performed in the root area to obtain composite propellers. The fiber of the propeller blade formed after assembly is discontinuous at the blade root, which is the key part of the propeller blade bearing force; the combined propeller has a secondary interface during the assembly process, and vibration fatigue is prone to occur during the motion process. Patent CN101704302 relates to a propeller blade mold manufacturing method suitable for RTM injection molding process. Through mold design and fiber preform laying, the resin is injected under a pressure of 50-60MPa. T...

Claims

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Application Information

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IPC IPC(8): B29C70/34B29C70/70
Inventor 郭浩昌吴医博李想
Owner 725TH RES INST OF CHINA SHIPBUILDING INDAL CORP
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