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Ceramic-metal composite material mixed multilayer material

A technology of composite materials and multilayer materials, which is applied in the field of ceramic-metal-composite hybrid multilayer materials, can solve the problems of low oxidation resistance, low strength and hardness, limited application fields, and easy oxidation, etc., to achieve notch sensitivity Reduce, increase strength and toughness, improve the effect of strength and toughness

Inactive Publication Date: 2017-10-03
SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the pure Glare laminates are not outstanding in high temperature resistance, oxidation resistance and strength and hardness. They are easily oxidized at high temperatures and easy to bend under load, thus limiting their application fields.

Method used

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  • Ceramic-metal composite material mixed multilayer material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0012] A ceramic-metal-composite hybrid multilayer material is characterized in that it is composed of C / SiC material, metal sheet and Glare laminate, and its structure is a laminated structure, from top to bottom followed by C / SiC material, metal sheet and Glare laminates. The thickness of the C / SiC material is 2 mm. The metal sheet is Mo metal material with a thickness of 0.4mm. The thickness of the Glare laminate is 3mm.

Embodiment 2

[0014] A ceramic-metal-composite hybrid multilayer material is characterized in that it is composed of C / SiC material, metal sheet and Glare laminate, and its structure is a laminated structure, from top to bottom followed by C / SiC material, metal sheet and Glare laminates. The thickness of the C / SiC material is 3 mm. The metal sheet is Ti metal material with a thickness of 0.3mm. The thickness of the Glare laminate is 4mm.

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Abstract

The invention discloses a ceramic-metal composite material mixed multilayer material which consists of a C / SiC material, sheet metal and a Glare laminate, and has a laminated structure. The C / SiC material, the sheet metal and the Glare laminate are sequentially arranged from top to bottom. The thickness of the C / SiC material is 1-4 mm; the sheet metal can be Mo, Nb or Ti and one of other alloy materials, and the thickness is 0.3-0.5 mm; and the thickness of the Glare laminate is 2-5 mm. According to a high-temperature hot press molding method, the material disclosed by the invention integrates the advantages of a ceramic-based composite material, the metal material and the Glare plate, so that the toughness of the material is obviously improved, the notch sensitivity is greatly improved, and the strength and toughness of the material are greatly improved.

Description

technical field [0001] The invention relates to a multilayer material, in particular to a ceramic-metal-composite hybrid multilayer material. Background technique [0002] At present, C / SiC composite materials can resist high temperature and oxidation, and have excellent high temperature performance. They are widely used in aircraft engines, brake discs, structural stress parts and other fields. scope of its use. Even through carbon fiber toughening, its toughness can reach alloy level, but due to the high notch sensitivity of silicon carbide material, the critical defect of fracture is too low, about 10 -3 The order of mm is far below the critical value of defects in metals and their alloys (about 1 mm level), but this fatal weakness greatly limits its wider application. The refractory metal has high strength and high toughness, and its fracture critical defect is much higher than that of silicon carbide ceramics. Due to the long-range orderly arrangement of metal atoms a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B9/00B32B9/04B32B15/00B32B15/04B32B17/02B32B17/06B32B7/08B32B33/00
CPCB32B9/005B32B7/08B32B9/041B32B15/043B32B15/14B32B33/00B32B2260/021B32B2262/101B32B2307/50
Inventor 潘影其他发明人请求不公开姓名
Owner SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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