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High-temperature brazed connection method for C/C composite material and nickel-based high-temperature alloy

A technology for nickel-based superalloys and composite materials, which is applied in the field of brazing connection between C/C composite materials and nickel-based superalloys, and can solve the problem of difficult wetting of nickel-based alloys, large differences in physical and chemical properties, and poor chemical compatibility. problem, to achieve the effect of good connection and alleviation of thermal expansion coefficient mismatch problem

Active Publication Date: 2015-01-28
无锡博智复合材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The difficulty of connecting C / C composite materials with nickel-based superalloys lies in: (1) the physical and chemical properties of the two are greatly different, the chemical compatibility is poor, and the nickel-based alloy is difficult to wet the interface of C / C composite materials; (2) nickel The thermal expansion coefficient of the alloy (12.5-16.3×10 -6 / K,20-1000℃) and the thermal expansion coefficient of C / C composite material (0-2.2×10 -6 / K, 20-2000°C), the difference is too large, resulting in a large thermal stress on the joint during the cooling process, which induces cracks to occur at or near the interface of the joint, eventually leading to premature failure and fracture of the joint

Method used

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  • High-temperature brazed connection method for C/C composite material and nickel-based high-temperature alloy

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] A 15mm×10mm×4mm C / C composite material and a nickel-based superalloy of equal size were brazed at 1160°C.

[0024] Step 1: Grind and polish the C / C composite material with No. 320 and No. 600 water sandpaper, then ultrasonically clean it in anhydrous ethanol for 30 minutes, and finally dry it in an oven at 80°C for 60 minutes before use.

[0025] Step 2, preparing a SiC coating on the surface of the C / C composite material by an embedding method.

[0026] Step 3, brazing connection of the C / C composite material and the nickel-based alloy. Specific process:

[0027] 1) Grind and polish the surface of the nickel-based superalloy to be connected with sandpaper, then clean the surface of the nickel-based superalloy to be connected with absolute ethanol, and dry it in an oven at 80°C for 30 minutes;

[0028] 2) Weigh an appropriate amount of BNi71CrSi solder and mix it with alcohol, and stir until uniform;

[0029] 3) Coat the BNi71CrSi slurry evenly on the surface-modifie...

Embodiment 2

[0037] A 25mm×10mm×6mm C / C composite material and a nickel-based superalloy of equal size were brazed at 1170°C.

[0038] Step 1: Grind and polish the C / C composite material with No. 320 and No. 600 water sandpaper, then ultrasonically clean it in absolute ethanol for 60 minutes, and finally dry it in an oven at 100°C for 50 minutes before use.

[0039] Step 2, preparing a SiC coating on the surface of the C / C composite material by an embedding method.

[0040] Step 3, brazing connection of the C / C composite material and the nickel-based alloy. Specific process:

[0041] 1) Grind and polish the surface of the nickel-based superalloy to be connected with sandpaper, then clean the surface of the nickel-based superalloy to be connected with absolute ethanol, and dry it in an oven at 100°C for 30 minutes;

[0042] 2) Weigh an appropriate amount of BNi71CrSi solder and mix it with alcohol, and stir until uniform;

[0043] 3) Coat the BNi71CrSi slurry evenly on the surface-modified...

Embodiment 3

[0051] A 10mm×10mm×4mm C / C composite material and a nickel-based superalloy of equal size were brazed at 1180°C.

[0052] Step 1: Grind and polish the C / C composite material with No. 320 and No. 600 water sandpaper, then ultrasonically clean it in absolute ethanol for 30 minutes, and finally dry it in an oven at 100°C for 40 minutes before use.

[0053] Step 2, preparing a SiC coating on the surface of the C / C composite material by an embedding method.

[0054] Step 3, brazing connection of the C / C composite material and the nickel-based alloy. Specific process:

[0055] 1) Grind and polish the surface of the nickel-based superalloy to be connected with sandpaper, then clean the surface of the nickel-based superalloy to be connected with absolute ethanol, and dry it in an oven at 120°C for 30 minutes;

[0056] 2) Weigh an appropriate amount of BNi71CrSi solder and mix it with alcohol, and stir until uniform;

[0057] 3) Coat the BNi71CrSi slurry evenly on the surface-modifi...

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Abstract

The invention discloses a high-temperature brazed connection method for a C / C composite material and nickle-based high-temperature alloy. The method comprises the following steps: preparing a SiC coating on the surface of the C / C composite material through an embedding method, and cleaning and drying the C / C composite material having the surface modified and the nickel-based high-temperature alloy having the surface polished; uniformly spreading BNi71CrSi nickel-based brazing alloy on the surface of the C / C composite material having the surface modified to form a sandwich structure of the C / C composite material / BNi71CrSi and the nickel-based high-temperature alloy, and placing the structure in a vacuum hot-pressing furnace for connection. The method realizes the connection of the C / C composite material and nickel-based alloy, effectively relieves the problems of wettability and mismatch of thermal expansion coefficients of nickel alloy and the C / C composite material, lowers the residual stress between connectors, and enables the room-temperature shearing strength of a C / C composite material and a nickel-based alloy connector to reach 35.08 MPa.

Description

technical field [0001] The invention relates to a brazing connection method of a composite material and a metal, in particular to a brazing connection method of a C / C composite material and a nickel-based superalloy. Background technique [0002] C / C composite materials have low density, high specific strength, low expansion coefficient, good high temperature performance, ablation resistance, corrosion resistance and other excellent properties, and are widely used in aviation, aerospace, automobile and nuclear energy and other fields. However, the brittleness of C / C composite materials, the difficulty of processing into complex large parts and the complicated production process limit their application. Therefore, it is necessary to connect C / C composite materials with metals in many occasions. [0003] High-temperature nickel-based alloy is a kind of high-temperature alloy widely used in the aviation field at present. It has excellent comprehensive properties at medium and ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B37/02C04B41/87
Inventor 史小红张鑫卢锦华李贺军李克智
Owner 无锡博智复合材料有限公司
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