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Part preparation method with ti/tixaly/ti multilayer structure

A technology of multi-layer structure and parts, which is applied in the preparation of parts with multi-layer structure, and the field of parts preparation with Ti/TixAly/Ti multi-layer structure, can solve the problem of single part forming shape, high cost of preparation method, and inability to prepare multi-layer structure Complex parts and other problems, to achieve the effect of high production efficiency, low preparation cost, and high engineering application value

Inactive Publication Date: 2016-01-27
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The object of the present invention is to provide a kind of Ti / Ti x Al y / Ti multilayer structure parts preparation method to solve the technical problems of high cost of preparation methods in the prior art, single shape of parts, and inability to prepare complex parts with multilayer structure

Method used

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  • Part preparation method with ti/tixaly/ti multilayer structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] Step 1: Select two pure titanium plates and one pure aluminum plate, the size of which is 200 mm long x 250 mm wide x 0.1 mm thick. Use emulsion explosives to perform explosive welding on the plates, control a reasonable detonation velocity, and make a titanium / aluminum / titanium three-layer composite plate, and then perform annealing heat treatment after rolling and leveling to obtain a titanium / aluminum / titanium composite plate with a thickness of 0.2mm;

[0023] Step 2: Bending and deforming the annealed titanium / aluminum / titanium three-layer composite plate with a bending die on the press until the shape becomes V-shaped;

[0024] Step 3. Put the titanium / aluminum / titanium three-layer composite part into the mold, use helium to pressurize the surface of the part, and heat it. The hot pressing temperature is 650°C, the applied pressure is 2MPa, and the temperature is kept for 10h , the reaction of the aluminum layer is completely consumed, and TiAl is generated in the...

Embodiment 2

[0026] Step 1. Select two pure titanium plates and one pure aluminum plate, the size of which is 300 mm long x 350 mm wide x 0.5 mm thick. Use emulsion explosives to perform explosive welding on the plates, control a reasonable detonation velocity, and make a titanium / aluminum / titanium three-layer composite plate, and then perform annealing heat treatment after rolling and leveling to obtain a titanium / aluminum / titanium composite plate with a thickness of 1.2mm;

[0027] Step 2. Perform liquid-filled deep drawing on the annealed titanium / aluminum / titanium three-layer composite plate on the hydraulic equipment until the shape becomes cylindrical, and reasonably control the liquid pressure to avoid the composite plate from breaking;

[0028] Step 3. Put the titanium / aluminum / titanium three-layer composite part into the mold, pressurize the surface of the part with neon gas, and heat it. The hot pressing temperature is 600°C, and the applied pressure is 2.5MPa. 15h, the aluminum ...

Embodiment 3

[0030] Step 1. Select three pure titanium plates and two pure aluminum plates, the size of which is 400mm long x 450mm wide x 0.3mm thick. Use emulsion explosives to explosively weld the plates, control a reasonable detonation velocity, and make a five-layer composite plate of titanium / aluminum / titanium / aluminum / titanium, and then perform annealing heat treatment after rolling and leveling to obtain titanium / aluminum with a total thickness of 0.7mm / titanium / aluminum / titanium five-layer composite board;

[0031] Step 2. Perform liquid-filled deep drawing on the annealed titanium / aluminum / titanium / aluminum / titanium five-layer composite plate on the hydraulic equipment until the shape becomes a box shape, and reasonably control the liquid pressure to avoid the composite plate from breaking;

[0032] Step 3. Put the titanium / aluminum / titanium / aluminum / titanium five-layer composite part into the mold, pressurize the surface of the part with argon gas, and heat it. The hot pressing...

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Abstract

The invention discloses a preparation method for a component with a Ti / Ti*Al y / Ti multilayer structure and belongs to the technical field of the preparation and forming of metal-based composite materials. The preparation method includes: firstly, using an explosive cladding method to prepare titanium / aluminum multilayer composite material, rolling, leveling, annealing and carrying out heat treatment; secondly, molding the metal composite laminate through a plastic forming method to obtain a component with complex shape; thirdly, putting the component in a die, pressurizing the surface of the component by means of inert gas, heating the component to react and consume the aluminum layer completely to generate a titanium-aluminum intermetallic compound layer, and obtaining the complex component with Ti / Ti*Al y / Ti multilayer structure finally. The preparation method for the component with the Ti / Ti*Al y / Ti multilayer structure overcomes the disadvantage that the traditional method is difficult to prepare the titanium-aluminum intermetallic compound component with complex structure and expands the application field of the titanium-aluminum intermetallic compound; the preparation cost is low, the production efficiency is high, and the engineering application value is very high.

Description

technical field [0001] The invention relates to a method for preparing parts with a multi-layer structure, specifically a method with Ti / Ti x al y The invention discloses a part preparation method of a Ti / Ti multilayer structure, belonging to the technical field of metal matrix composite material preparation and forming. Background technique [0002] The field of aerospace engineering is increasingly pursuing high specific strength and excellent high-temperature mechanical properties of materials. Single-component materials can no longer meet the relevant engineering needs. Therefore, the research and preparation of new composite materials has become the focus of attention in the field of aerospace engineering. At present, the most high-temperature materials used in aircraft are titanium alloys and Ni-based superalloys. Ni-based superalloys can be used at temperatures up to 700 ° C, but due to their high density and the inability to use them at higher temperatures, their...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/00
CPCB23P15/00
Inventor 郭训忠陶杰范敏郁
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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