High strength high elasticity heatproof titanium alloy and preparation method thereof

A titanium alloy and high-elasticity technology, which is applied in the design and preparation of titanium alloy materials, can solve the problems that cannot meet the performance requirements of heat-resistant elastic parts of hypersonic aircraft, and achieve the effect of improving strength

Active Publication Date: 2018-10-19
SOUTHEAST UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the traditional high-strength titanium alloy Ti-10V-2Fe-3Al (Ti-10-2-3) and the low elastic modulus titanium alloy Ti-11.5Mo-6Zr-4.5Sn (Beta-Ⅲ) after aging at about 500 ℃ , whose E values ​​are all over 95GPa, σ 0.2 / E is less than 1.3%, which cannot meet the performance requirements of heat-resistant elastic parts of hypersonic aircraft

Method used

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  • High strength high elasticity heatproof titanium alloy and preparation method thereof
  • High strength high elasticity heatproof titanium alloy and preparation method thereof
  • High strength high elasticity heatproof titanium alloy and preparation method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0033] With high purity Ti, Nb, V, Zr and TiO 2 (TiO 2 , Ti: 60%; O: 40%) as the raw material to prepare the alloy, the weight of each component is: Nb: 34.7wt%; V: 0.2wt%; Zr: 1.8wt%; O: 0.30wt%, the balance is Ti. The prepared raw materials are smelted five times in a magnetic stirring vacuum non-consumable arc furnace to obtain an ingot with uniform composition. The ingot was hot forged into a bar at 800°C with a deformation of 85%. After solution treatment at 1000℃ for 50min, it was put into water for quenching and cooling. The bar surface is descaled by turning, and then cold rolled with 80% deformation at room temperature. The rods were placed in a quartz tube to be vacuum-sealed, heated to 490°C for 10h in a heat treatment furnace, and then cooled to room temperature in air. Mechanical properties are: σ b =1131.5MPa, σ 0.2 =1042.5MPa, E=69.5GPa, σ 0.2 / E=1.50%, δ=11.7%.

Embodiment 2

[0035] With high purity Ti, Nb, V, Zr and TiO 2 (TiO 2 , Ti: 60%; O: 40%) as the raw material to prepare the alloy, the weight of each component is: Nb: 32.0wt%; V: 2.0wt%; Zr: 2.2wt%; O: 0.31wt%, the balance is Ti. The prepared raw materials are smelted five times in a magnetic stirring vacuum non-consumable arc furnace to obtain an ingot with uniform composition. The ingot was hot forged into a bar at 830°C with a deformation of 75%. After solution treatment at 970℃ for 55min, it was put into water for quenching and cooling. Turning to remove scale on the surface of the bar, followed by cold rolling at room temperature with a deformation of 85%. The rods were placed in a quartz tube to be vacuum-sealed, heated to 510 °C in a heat treatment furnace for 9 h, and then cooled to room temperature in air. Mechanical properties are: σ b =1149.3MPa, σ 0.2 =1058.5MPa, E=70.1GPa, σ 0.2 / E=1.51%, δ=11.0%.

Embodiment 3

[0037] With high purity Ti, Nb, V, Zr and TiO 2 (TiO 2 , Ti: 60%; O: 40%) as the raw material to prepare the alloy, the weight of each component is: Nb: 29.0wt%; V: 4.0wt%; Zr: 2.0wt%; O: 0.30wt%, the balance is Ti. The prepared raw materials are smelted five times in a magnetic stirring vacuum non-consumable arc furnace to obtain an ingot with uniform composition. The ingot was hot forged into a bar at 900°C with a deformation of 80%. After solution treatment at 930℃ for 55min, it was put into water for quenching and cooling. The bar surface is descaled by turning, and then subjected to cold rolling deformation at room temperature with a deformation amount of 90%. The bar was placed in a quartz tube to be vacuum-sealed, heated to 510 °C in a heat treatment furnace for 8 h, and then cooled to room temperature in air. Mechanical properties are: σ b =1134.8MPa, σ 0.2 =1046.5MPa, E=68.4GPa, σ 0.2 / E=1.53%, δ=11.4%.

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Abstract

The invention relates to a high strength high elasticity heatproof titanium alloy and a preparation method thereof. The alloy comprises Ti, Nb, Zr, V, and O, wt%Nb=35wt%-1.5wt%V, wt%Nb represents weight percentage of Nb, wt%V represents weight percentage of V, V: 0 wt%<V<=4.0 wt%, Zr: 1.8-2.2 wt%, O: 0.29-0.31 wt%, and the balance being Ti. The preparation method comprises following steps: carrying out smelting in a vacuum non-consumable electric arc furnace to obtain uniform alloy ingots; carrying out hot forging to obtain rods, performing a solution treatment at a temperature of 900-1000 DEGC, cooling to the room temperature; carrying out cold rolling and deformation processing, wherein the deformation amount is 80-90%; and finally carrying out an aging heat treatment, wherein the heating temperature is 490 to 510 DEG C, and the holding time is 8-10 hours. The titanium alloy has the advantages of high strength and low elastic modulus, the elastic deformation capacity (the ratio of yield strength to elastic modulus) is better than those of various high elasticity beta-titanium alloys, and thus the titanium alloy is very suitable for preparing light, heatproof, and high elasticityparts in the fields of aviation, aerospace, and machinery.

Description

technical field [0001] The invention relates to a high-strength, high-elasticity, heat-resistant titanium alloy and a preparation method, and belongs to the technical field of titanium alloy material design and preparation. Background technique [0002] In recent years, hypersonic vehicles have become one of the research hotspots in the field of aerospace in my country. Such vehicles with flying speeds exceeding 5 times the speed of sound have great military value and potential economic value. In the development of hypersonic aircraft, the research and development of lightweight, heat-resistant and highly elastic materials for deformable wings is a major difficulty, because during the flight of such aircraft, due to the effect of aerodynamic thermal loads, the The temperature of the leading edge of the wing is as high as 400-500 °C, and the wing material must be heat-resistant; on the other hand, in order to reduce the weight, simplify the driving mechanism and maximize the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C14/00C22C1/02C22F1/18
CPCC22C1/02C22C14/00C22F1/183
Inventor 陈锋陈慧娟余新泉张友法
Owner SOUTHEAST UNIV
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