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Forming die for cylindrical composite component with flanging and preparation method

A technology for composite material components and forming molds, which is applied in the direction of molds, ceramic molding machines, mold fixing devices, etc., and can solve problems such as difficult operation, less research, and inability to uniformly pressurize

Active Publication Date: 2020-07-07
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the relatively mature curing method of ceramic matrix composites is molding and shaping, but due to the inability to uniformly pressurize and the difficulty of operation, this method is not suitable for the preparation of variable-section cylindrical components with flanges.
In addition, the key technology of prepreg-infiltration process to prepare ceramic matrix composites has just been broken through in China in recent years, and there are relatively few studies on the use of prepregs to prepare ceramic matrix composite components.

Method used

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  • Forming die for cylindrical composite component with flanging and preparation method
  • Forming die for cylindrical composite component with flanging and preparation method
  • Forming die for cylindrical composite component with flanging and preparation method

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Embodiment Construction

[0040] The molding die and preparation method of the cylindrical composite material member with flanging will be described below in conjunction with the accompanying drawings and specific examples.

[0041] Such as figure 2 As shown, in this embodiment, the end surface of the cylindrical member with flanging is a circular bottom surface, and the side surface is a cylindrical structure connected by a cone and a cylinder. The molding die for this kind of ceramic matrix composite member includes:

[0042] One end of the core barrel 2 is a tapered cylindrical structure with a taper of 2o, and the other end is a cylindrical structure. The outer surface of the cone is consistent with the inner surface of the insert 1; the diameter of the outer surface of the cylinder is 10mm larger than the diameter of the large end of the cone. At the junction of the cylinder and the cone, the insert is axially positioned by an axial positioning platform, and the surface of the core barrel 2 is re...

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Abstract

The invention relates to a forming die for cylindrical composite component with flanging and a preparation method. The die comprises a core barrel, an insert, an end cover, a flange shaft, a pressureleveling plate and a demolding tool. The demolding tool comprises a demolding frame and a top plate. By means of the technical scheme of the forming die for the cylindrical composite component with the flanging and the preparation method, the problem that the difficulty of forming a variable-section cylindrical ceramic-based composite material thin-wall component with flanging is large can be solved. Sufficient forming pressure can be provided for prepreg in the forming process, so that each profile surface of a component is uniformly stressed, and the defects of the component are avoided. Through the block insert design and the demolding tool, it is ensured that the component can be safely and smoothly removed from a mold after formed, and the forming quality and the forming efficiency ofthe component are improved.

Description

technical field [0001] The invention relates to a molding die for a cylindrical composite material component with flanging and a preparation method thereof, belonging to the technical field of composite material molding and manufacturing. Background technique [0002] Due to its excellent high temperature resistance, oxidation resistance, corrosion resistance and low density, ceramic matrix composites have important applications in aerospace and other fields, especially in the field of aeroengines. preferred. At present, enterprises represented by GE in the United States have successfully realized the mass production of ceramic matrix composite materials, and prepared different materials such as combustion chambers, flame tubes, exhaust mixers, turbine guide vanes, turbine outer rings, and tail nozzle central bodies. The components of the structure, and successfully realized commercial applications on LEAP and other types of aero-engines. [0003] Ceramic matrix composites...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B28B23/02B28B13/06B28B7/18B28B7/00
CPCB28B7/0002B28B7/0011B28B7/0014B28B7/18B28B13/06B28B23/02
Inventor 高晔焦健姜卓钰杨金华周怡然
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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