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Machining method for improving obdurability of two-phase titanium alloy large-size bar

A processing method and titanium alloy technology, which is applied in the field of titanium alloy processing, can solve the problems of low Widmanstatten tissue plasticity and low damage tolerance performance, and achieve the effect of increasing crystal cores, uniform distribution, and uniform alloy composition

Active Publication Date: 2013-02-27
西安秦钛智造科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, due to the low plasticity of the Widmanstatten structure due to the coarse primary grains and the existence of α-phase at the grain boundary, it is usually not used
For structural parts used in aerospace, equiaxed or bimodal structures are mostly used, but the damage tolerance performance of such structures obtained by traditional thermal processing is low

Method used

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  • Machining method for improving obdurability of two-phase titanium alloy large-size bar
  • Machining method for improving obdurability of two-phase titanium alloy large-size bar

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] In this embodiment, the processing method for improving the strength and toughness of the two-phase titanium alloy large-size bar comprises the following steps:

[0026]Step 1: Carry out billet forging of the TC4 two-phase titanium alloy ingot, and obtain the first forging billet after water cooling; the cross-section of the two-phase titanium alloy ingot is a circle with a diameter of 460 mm; the cross-section of the first forging billet is It is a circle with a diameter of 320mm; the blank forging is completed in two times by upsetting and drawing, and the deformation of each blank forging is 80%, and the two-phase titanium The alloy ingot is subjected to the first-stage heat treatment, wherein the temperature of the first-stage heat treatment before the first billet forging is 150°C above the β transformation point, and the first-stage heat treatment is carried out before the first billet forging The time is 368min, the final forging temperature of the first billet f...

Embodiment 2

[0037] In this embodiment, the processing method for improving the strength and toughness of the two-phase titanium alloy large-size bar comprises the following steps:

[0038] Step 1: Carry out billet forging of the TC6 two-phase titanium alloy ingot, and obtain the first forging billet after water cooling; the cross-section of the two-phase titanium alloy ingot is a circle with a diameter of 600mm; the cross-section of the first forging billet It is a circle with a diameter of 480mm; the blank forging is completed in two times by upsetting and drawing, and the deformation of each blank forging is 85%, and the two-phase titanium The alloy ingot is subjected to the first stage of heat treatment, wherein the temperature of the first stage of heat treatment before the first billet forging is 160°C above the β transformation point, and the first stage of heat treatment is carried out before the first billet forging The time for 600min is 600min, the final forging temperature of t...

Embodiment 3

[0045] In this embodiment, the processing method for improving the strength and toughness of the two-phase titanium alloy large-size bar comprises the following steps:

[0046] Step 1: Carry out billet forging of the TC11 two-phase titanium alloy ingot, and obtain the first forging billet after water cooling; the cross-section of the two-phase titanium alloy ingot is a circle with a diameter of 800mm; the cross-section of the first forging billet It is a circle with a diameter of 620mm; the billet forging is completed in two times by upsetting and drawing, and the deformation of each billet forging is 90%, and the two-phase titanium The alloy ingot is subjected to the first stage of heat treatment, wherein the temperature of the first stage of heat treatment before the first billet forging is 180°C above the β transformation point, and the first stage of heat treatment is carried out before the first billet forging The time is 800min, the final forging temperature of the first...

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Abstract

The invention provides a machining method capable of improving the obdurability of a two-phase titanium alloy large-size bar, comprising the following steps of: 1, performing cogging forging on a two-phase titanium alloy cast ingot; 2, performing primary upsetting-drawing forging; 3, performing homogenization treatment; 4, performing secondary upsetting-drawing forging; and 5, performing annealing treatment on a finished product to obtain the two-phase titanium alloy large-size bar having a diameter of 250-450 mm. The two-phase titanium alloy large-size bar prepared by the machining method disclosed by the invention has a certain equiaxial alpha-phase content, original beta-crystalline grains are uniform and fine, and secondary alpha-strips are of a duplex organization structure with a certain length-width ratio, so that the flaw detection level of the large-size bar is raised while the strength and the fracture toughness of alloy is improved; and the two-phase titanium alloy large-size bar prepared by the machining method disclosed by the invention is good in obdurability.

Description

technical field [0001] The invention belongs to the technical field of titanium alloy processing, and in particular relates to a processing method for improving the strength and toughness of two-phase titanium alloy large-size rods. Background technique [0002] Titanium alloy has become the key structural material of aviation and aerospace vehicles due to its excellent characteristics such as high specific strength and good corrosion resistance. With the improvement of aircraft performance, the amount of titanium used in the body structure is increasing. At present, the amount of titanium used in the most representative F-22 fighter jet reaches 41% of the structural weight, and the amount of titanium used in the latest large Boeing 787 has also reached 15% of the weight of the structure. Since the 1960s, high reliability and long life have become the development direction of material selection and design and manufacture of aerospace structural parts. The design concept has...

Claims

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Application Information

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IPC IPC(8): C22F1/18
Inventor 韩栋赵永庆毛小南洪权郭萍贾蔚菊
Owner 西安秦钛智造科技有限公司
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