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Vacuum active brazing process for C/C or C/SiC composite material and metal

A composite material and active brazing technology, which is applied in the field of heterogeneous material connection, can solve the problems of complex structure of connecting parts, heavy weight of thrust chamber, poor sealing performance, etc., and achieve high production efficiency, high connection strength and good air tightness Effect

Active Publication Date: 2010-06-16
GRIMAT ENG INST CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Traditional C / C or C / SiC composite nozzles are mechanically connected to the metal head. The connection made by this method is complex in structure, heavy in the thrust chamber, and has disadvantages such as poor sealing and low reliability.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] Connection between C / SiC and C103(89Nb-10Hf-1Ti) niobium alloy:

[0016] 1. Surface pretreatment of C / SiC welding area: use diamond grinding wheel to grind the surface of C / SiC composite material welding area, the processing volume is 0.2mm, after the processing is completed, ultrasonic cleaning in acetone solution for 30min, after hot air drying Carry out vacuum heat treatment, vacuum degree 5Pa, temperature 1100 ℃, time 60min;

[0017] 2. Cleaning of AgCuTi active solder: Take a sheet of AgCuTi active solder with a thickness of 0.1 mm, ultrasonically clean it in acetone solution for 30 minutes, then clean it with a large amount of deionized water, and dry it for use;

[0018] 3. Cleaning of the welded metal C103 niobium alloy: First, boil it in an alkaline solution at 60°C for 8 minutes for degreasing treatment, rinse it with deionized water, and then put it into a mixed solution of nitric acid, hydrofluoric acid, hydrochloric acid, and deionized water. Wash for 50s ...

Embodiment 2

[0022] Brazing C / SiC and C103 niobium alloy with oxygen-free copper as metal transition layer:

[0023] 1. Surface pretreatment of C / SiC welding area: use diamond grinding wheel to grind the surface of C / SiC composite material welding area, the processing volume is 0.2mm, after the processing is completed, ultrasonic cleaning in acetone solution for 30min, after hot air drying Carry out vacuum heat treatment, vacuum degree 5Pa, temperature 1100 ℃, time 40min;

[0024] 2. Cleaning of AgCuTi active solder: take a sheet of AgCuTi active solder with a thickness of 0.1 mm, polish its surface with sandpaper, clean it with ultrasonic waves in acetone solution for 30 minutes, and then clean it with a large amount of deionized water. drying in an oven;

[0025] 3. Cleaning of the welded metal C103 niobium alloy: First, boil it in an alkaline solution at 60°C for 8 minutes for degreasing treatment, rinse it with deionized water, and then put it into a mixed solution of nitric acid, hyd...

Embodiment 3

[0030] C / C and titanium alloy Ti 6 al 4 Connection of V:

[0031] 1. Surface pretreatment of C / C welding area: use diamond grinding wheel to grind the surface of C / C composite material welding area, the processing volume is 0.1mm, after the processing is completed, ultrasonic cleaning in acetone solution for 30min, and hot air drying Carry out vacuum heat treatment, vacuum degree 5Pa, temperature 1200 ℃, time 30min;

[0032] 2. Cleaning of CuAlSiTi active solder: take a sheet-shaped CuAlSiTi active solder with a thickness of 0.1 mm, polish its surface with sandpaper, clean it with a large amount of deionized water after ultrasonic cleaning in acetone solution, and bake it at 70-80 °C dry for use;

[0033] 3. Cleaning of the titanium alloy to be welded: First, boil it in an alkali solution at 80°C for 8 minutes for degreasing treatment, rinse it with deionized water, and then pickle it in a mixed solution of nitric acid, hydrofluoric acid and deionized water for 60 seconds ...

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Abstract

The invention discloses a vacuum active brazing process for a C / SiC or C / C composite material and metal, which belongs to the technical field of connection of heterostructure materials. The process comprises the following steps of: respectively pretreating a composite material, brazed material and an active brazing material and then placing the active brazing material between the brazed composite material and the metal; vertically applying seal pressure; and then placing a workpiece to be brazed into a vacuum brazing furnace to carry out vacuum brazing. When a difference of the composite material and a metal thermal expansion coefficient is larger, the seal stress is relieved by clamping a metal transition layer between double layers of brazing materials. The invention has the characteristics that by carrying out high-temperature vacuum heat treatment on the composite material, the condition that a volatile matter of the composite material influences the seal quality of the brazing material during vacuum brazing is prevented; the active brazing material and the composite material directly generate physical and chemical reaction, and the gas tightness is good; the seal stress is released by the plastic deformation of transition metal, and the connecting strength is high.

Description

technical field [0001] The invention belongs to the technical field of heterogeneous material connection, in particular to a vacuum active brazing process of C / C or C / SiC composite material and metal. Background technique [0002] Carbon fiber reinforced carbon (C / C) composite materials and carbon fiber reinforced silicon carbide (C / SiC) composite materials have low density (general density 1.75 ~ 2.10g / cm 3 ), light weight, outstanding high-temperature mechanical properties (high strength, high modulus, excellent fracture toughness and wear resistance, erosion resistance, good thermal stability, low thermal expansion coefficient, high thermal conductivity), etc., is an ideal space vehicle thrust chamber nozzle material. The traditional C / C or C / SiC composite nozzle is mechanically connected to the metal head. The connection made by this method is complex in structure, heavy in the thrust chamber, and has disadvantages such as poor sealing and low reliability. Contents of...

Claims

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Application Information

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IPC IPC(8): C04B37/02
Inventor 陆艳杰张小勇楚建新
Owner GRIMAT ENG INST CO LTD
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