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Laminated composite material fan blade and reinforcing method thereof

A composite material, fan blade technology, applied in wind power generation, liquid fuel engine, final product manufacturing, etc., can solve the problems of brittle fracture, difficult to meet requirements, and discount of interlayer performance enhancement effect.

Pending Publication Date: 2022-07-08
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Z-Pin technology can effectively enhance the interlayer performance of laminated composite materials, but the traditional Z-Pin is made of carbon fiber and implanted with the aid of an ultrasonic hammer. The implantation depth is difficult to exceed 5mm, and the in-plane performance of the laminated composite material is damaged. As high as 15%-25% or more, and carbon fiber Z-Pin often undergoes brittle fracture under high strain rate loads such as bird strikes, which greatly reduces the effect of enhancing interlayer performance
The thickness of the tenon is as high as 50-80mm or more, and the Z-Pin implantation depth needs to be more than 20mm to suppress the delamination of key positions in the structural layer under centrifugal load and high-cycle vibration fatigue load. It is difficult to meet the requirements

Method used

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  • Laminated composite material fan blade and reinforcing method thereof
  • Laminated composite material fan blade and reinforcing method thereof
  • Laminated composite material fan blade and reinforcing method thereof

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Embodiment Construction

[0024] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description to facilitate a full understanding of the present invention, but it is obvious that the present invention can be implemented in many other ways that are different from those described herein. Those skilled in the art can make similar promotions and deductions according to the actual application situation without violating the connotation of the present invention. Therefore, the content of the specific embodiments should not limit the protection scope of the present invention.

[0025] like figure 1 As shown, Z-Pin with different densities is implanted in different areas around the fan blade of the laminated composite material. Z-pin is a kind of Z-Pin used for pinning into uncured prepreg or fiber preform. The thickness direction of the composite material forms an anchored and toughened micro rod....

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Abstract

The invention aims to provide the fan blade made of the laminated composite material and the reinforcing method of the fan blade. The blade structure or the reinforcing method can enhance the interlayer performance of the laminated composite material. In order to achieve the purpose, Z-Pin is implanted into the laminated composite material fan blade, the Z-Pin is organic fibers, and the Z-Pin is implanted in a pre-perforation implantation mode.

Description

technical field [0001] The present invention relates to a laminated composite fan blade and a method for strengthening the same. Background technique [0002] Laminated composite fan blades are an important technical approach to reduce the weight and noise of high bypass ratio aviation turbofan engines. Bird strike resistance and centrifugal strength are the two most important performance indicators of composite fan blades. A large number of test and simulation data show that the bird strike and centrifugal strength of laminated composite fan blades, as well as the high-cycle vibration fatigue closely related to centrifugal strength, all take delamination as the first failure mode, and the overall bending stiffness of the blade after delamination It is reduced to less than 1 / 4 of that before delamination, and then bending compression and tensile fracture occur under bird strike load. Tenon delamination in centrifugal strength tests puts the blade at risk of being pulled ou...

Claims

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Application Information

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IPC IPC(8): F02K3/04F04D29/02F04D29/38F04D29/58
CPCF02K3/04F04D29/384F04D29/388F04D29/584F04D29/023Y02P70/50
Inventor 张婷冯锦璋李向前陈巍司武林姜晓伟
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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