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

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

Active Publication Date: 2013-11-27
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] The 15mm×10mm×4mm C / C composite material and the nickel-based superalloy of equal size were brazed and connected at 1160℃.

[0024] Step 1. Grind and polish the C / C composite material with No. 320 and No. 600 water sandpaper, then put it in absolute ethanol for ultrasonic cleaning for 30 minutes, and finally dry it in an oven at 80°C for 60 minutes.

[0025] Step 2: Prepare SiC coating on the surface of C / C composite material by embedding method.

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

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

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

[0029] 3) Coat the BNi71CrSi slurry uniformly on the surface-modified C / C compos...

Embodiment 2

[0037] The 25mm×10mm×6mm C / C composite material and the nickel-based superalloy of the same size were brazed and connected at 1170°C.

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

[0039] Step 2: Prepare SiC coating on the surface of C / C composite material by embedding method.

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

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

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

[0043] 3) Coat the BNi71CrSi slurry uniformly on the surface-modified C / C ...

Embodiment 3

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

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

[0053] Step 2: Prepare SiC coating on the surface of C / C composite material by embedding method.

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

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

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

[0057] 3) Coat the BNi71CrSi slurry uniformly on the surface-modified C / C com...

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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 between a composite material and a metal, in particular to a brazing connection method between a C / C composite material and a nickel-based high-temperature alloy. Background technique [0002] C / C composite materials have excellent properties such as low density, high specific strength, low expansion coefficient, good high temperature performance, ablation resistance, and corrosion resistance, and are widely used in aviation, aerospace, automotive and nuclear energy fields. However, the brittleness of C / C composite material itself, the difficulty of processing into complex large parts, and the complicated production process, all limit its application. Therefore, it is necessary to connect C / C composite materials with metal in many occasions. [0003] High temperature nickel-based alloy is currently a kind of high temperature alloy widely used in the aviation field. It has excellent comprehensive properties...

Claims

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Application Information

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Patent Type & Authority Applications(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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