A method for assisting brazing of a graphene sponge intermediate layer

A technology of graphene sponge and intermediate layer, which is applied in welding equipment, welding medium, welding/cutting medium/material, etc., can solve the problems of large residual stress and low reliability, achieve continuous reaction layer, improve mechanical properties, reduce The effect of joint stress concentration

Active Publication Date: 2020-07-07
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The present invention aims to solve the technical problem of low reliability caused by large residual stress in the existing C / C composite brazing connection, thereby providing a method for assisting brazing of a graphene sponge intermediate layer

Method used

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  • A method for assisting brazing of a graphene sponge intermediate layer
  • A method for assisting brazing of a graphene sponge intermediate layer

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Experimental program
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specific Embodiment approach 1

[0022] Specific embodiment one: present embodiment a kind of method for auxiliary brazing of graphene sponge intermediate layer, specifically carry out according to the following steps:

[0023] 1. Cut the C / C composite material into thin slices with a thickness of 2-3 mm, then polish the parts to be welded with sandpaper, and then put them into acetone solution for ultrasonic cleaning to obtain the C / C composite material to be welded;

[0024] 2. Cut the graphene sponge into thin slices along the direction parallel to the cross section to obtain the middle layer of the graphene sponge;

[0025] 3. At room temperature, the AgCuTi powder brazing filler metal is subjected to sheeting treatment to obtain a button-shaped brazing filler metal sheet with a diameter of 8-12 mm;

[0026] Four, the graphene sponge intermediate layer that step 2 obtains and the solder sheet that step 3 obtains are stacked between two C / C composite materials to be welded that step 1 obtains and assemble,...

specific Embodiment approach 2

[0028] Embodiment 2: This embodiment is different from Embodiment 1 in that: In step 1, a wire electric discharge machine is used to cut the C / C composite material. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0029] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that in step one, 240#, 600# and 1000# sandpapers are used successively to polish the parts to be welded. Others are the same as in the first embodiment.

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Abstract

The invention discloses a method for assisting in soldering a graphene sponge intermediate layer, and relates to the field of methods for soldering C / C composite materials. The method aims to solve the technical problem of low reliability caused by large residual stress in the prior C / C composite material soldering connection. The method comprises the steps of: (1) cutting the C / C composite materials and performing cleaning; (2) cutting graphene sponge into slices in a direction parallel to the cross section; (3) tabletting AgCuTi powder solders; (4) performing assembling and compacting; and (5) performing soldering. According to the method, through the in-situ reaction between the graphene sponge intermediate layer and Ti in the solders, uniformly distributed TiC reinforcing phases are generated in soldering seams, a soldering seam matrix structure is refined and reinforced, and brittle Cu2Ti is prevented from being formed in the soldering seams, so that the mechanical property of anobtained joint is improved, and the shear strength can reach 55 MPa. The method is used in the field of C / C composite material soldering connection.

Description

technical field [0001] The invention relates to the field of methods for brazing C / C composite materials. Background technique [0002] With the rapid development of space technology, people explore and develop space more and more frequently, and the performance and quantity of rockets carrying various space stations and space probes continue to develop accordingly. The nozzle plays an important role in the energy conversion of the rocket engine, and it often needs to withstand harsh service conditions when the nozzle of the rocket engine is working. First of all, under service conditions, the nozzle is in a high-temperature environment of 2000°C to 3500°C, and must withstand severe thermal shock. In addition, high temperature service environment often brings higher thermal stress caused by thermal gradient. The high-velocity corrosive gas also makes its service environment more severe. High melting point metal is a traditional rocket nozzle material, but the disadvantage...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23K35/14B23K35/30B23K1/008B23K103/12
CPCB23K1/008B23K35/302
Inventor 孙湛曹雨张丽霞宋亚楠冯吉才
Owner HARBIN INST OF TECH
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