Heat strong titanium alloy ingot for aviation and manufacturing method for heat strong titanium alloy

A titanium alloy and aviation technology, applied in the field of titanium alloy materials, can solve the problems of large melting point temperature gradient of main elements, refractory blocks, etc., and achieve the effect of solving composition segregation, homogenizing composition, and improving composition uniformity

Active Publication Date: 2016-08-10
西部超导材料科技股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a kind of heat-strength titanium alloy ingot for aviation, which solves the problem that the main element melting point temperature gradient in the existing WSTi62411SC titanium alloy is large, and aluminum segregation and zirconium, niobium, molybdenum and silicon are easily formed when the ingot is smelted. The problem of metallurgical defects such as refractory lumps

Method used

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  • Heat strong titanium alloy ingot for aviation and manufacturing method for heat strong titanium alloy
  • Heat strong titanium alloy ingot for aviation and manufacturing method for heat strong titanium alloy
  • Heat strong titanium alloy ingot for aviation and manufacturing method for heat strong titanium alloy

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preparation example Construction

[0035] A kind of preparation method of the heat-strength titanium alloy casting ingot for aviation of the present invention, specifically comprises the following steps:

[0036] Step 1, according to the weight percentage of elements: 6.2% to 7.3% Al, 0.4% to 1.0% Mo, 3.5% to 4.5% Zr, 0.5% to 1.5% Nb, 2.0% to 3.0% Sn, 0.1% to 0.25% Si, 0.04% to 0.15% O, 0.05% to 0.14% C, the balance is Ti, the sum of the weight percentages of the above components is 100%, weigh 40Al55Mo5Ti alloy, Ti80Sn alloy, Ti50Si alloy, Nb47Ti alloy and 5-9mm particle size Small particles of zirconium sponge, aluminum beans, TiO 2 Powder, C powder and first-class small particle sponge titanium with a particle size of 5-10 mm are mixed with the above raw materials for a single electrode, and then pressed into an electrode block;

[0037] Step 2, the electrode block obtained in step 1 is welded into an electrode by using a non-tungsten argon shielded plasma box;

[0038] Step 3, put the electrode prepared i...

Embodiment 1

[0045] Step 1, according to the weight percentage of elements: 6.2% Al, 0.4% ~ 1.0% Mo, 4.5% Zr, 1.0% Nb, 2.0% Sn, 0.2% Si, 0.1% O, 0.08% C, the balance is Ti, the above group The sum of the percentages by weight is 100%, weigh 40Al55Mo5Ti alloy, Ti80Sn alloy, Ti50Si alloy, Nb47Ti alloy and small particles of zirconium sponge, aluminum beans, TiO 2 Powder, C powder and first-class small particle sponge titanium with a particle size of 5-10 mm are mixed with the above raw materials for a single electrode, and then pressed into an electrode block;

[0046] Step 2, the electrode block obtained in step 1 is welded into an electrode by using a non-tungsten argon shielded plasma box;

[0047] Step 3, put the electrode prepared in step 2 into a vacuum consumable electric arc furnace for two vacuum smelting. During the smelting process, the smelting speed is controlled by controlling the current. The parameters are as follows:

[0048]

[0049]

[0050] A heat-strength titanium...

Embodiment 2

[0052] Step 1, according to the weight percentage of elements: 7.3% Al, 0.8% Mo, 4.0% Zr, 0.5% Nb, 2.5% Sn, 0.25% Si, 0.04% O, 0.14% C, the balance is Ti, the weight percentage of the above components The sum is 100%, weigh 40Al55Mo5Ti alloy, Ti80Sn alloy, Ti50Si alloy, Nb47Ti alloy and small particles of zirconium sponge, aluminum beans, TiO 2 The powder and the first-class small particle sponge titanium with a particle size of 5-10 mm are mixed with the above raw materials for a single electrode, and then pressed into an electrode block;

[0053] Step 2, the electrode block obtained in step 1 is welded into an electrode by using a non-tungsten argon shielded plasma box;

[0054] Step 3, put the electrode prepared in step 2 into a vacuum consumable electric arc furnace for three times of vacuum smelting. During the smelting process, the smelting speed is controlled by controlling the current. The parameters are as follows:

[0055]

[0056]

[0057] A heat-strength tit...

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Abstract

The invention discloses a heat strong titanium alloy ingot. The heat strong titanium alloy ingot includes, by weight percentage, 6.2%-7.3% of Al, 0.4%-1.0% of Mo, 3.5%-4.5% of Zr, 0.5%-1.5% of Nb, 2.0%-3.0% of Sn, 0.1%-0.25% of Si, 0.04%-0.15% of O, 0.05%-0.14% of C and the balance Ti, and the sum of the weight percentages of the components is 100%. The invention further discloses a manufacturing method of the ingot. The component uniformity of the large ingot is improved by changing an adding manner of alloy elements, and a component uniformity control technology is successfully broken through; and meanwhile in the smelting process, the smelting speed is controlled by controlling current, the purpose of homogenizing the components is achieved, and the problem that when a conventional method is adopted for smelting WSTi62411SC titanium alloys, metallurgical defects that aluminum segregation exists and a molybdenum block is difficult to smelt are liable to be generated is effectively solved.

Description

technical field [0001] The invention belongs to the technical field of titanium alloy materials, and in particular relates to a heat-strength titanium alloy ingot for aviation, and also relates to a preparation method of the heat-strength titanium alloy ingot for aviation. Background technique [0002] WSTi62411SC titanium alloy is a deformation heat-strength titanium alloy, which belongs to near α-type titanium alloy. It is one of the most representative alloys in the Ti-Al-Zr-Sn-Mo-Nb-Si-C alloy system. Working at 550-600°C, it is used to manufacture compressor disks and blades of aero-engines, etc. It is improved from the BT18 alloy. While reducing the aluminum content, the modified alloy replaces part of the zirconium with tin, thus improving its process plasticity, thermal stability, creep resistance and impact toughness; while maintaining the 600 ℃ durable strength, but the instantaneous strength at the working temperature and the plasticity after heat preservation at...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C14/00C22C1/03
CPCC22C1/03C22C14/00
Inventor 赖运金史小云毛友川杜建超李芳朱静张鹏楼美琪王凯旋冯勇张平祥
Owner 西部超导材料科技股份有限公司
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