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TB17 titanium alloy isothermal forging method

A technology of isothermal forging and titanium alloy, applied in the field of warm forging, it can solve the problem that strength and toughness cannot be effectively matched.

Active Publication Date: 2022-03-25
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The purpose of the present invention is: for TB17 ultra-high strength titanium alloy, the prior art cannot effectively solve the contradictory problem that the strength and toughness cannot be effectively matched, and the present invention can An isothermal forging method that effectively improves the comprehensive mechanical properties of the alloy

Method used

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Examples

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Embodiment 1

[0019] This embodiment is for forging a nearly β-type TB17 titanium alloy forging with a phase transition point of 843°C.

[0020] The specific implementation process is as follows:

[0021] (1) Put the TB17 titanium alloy blank into the effective working area of ​​the resistance furnace that has reached the set heating temperature of 790°C for heating and heat preservation. The heat preservation time is 80 minutes, and then heat up to 873°C with the furnace, and then heat preservation for 40 minutes;

[0022] (2) Step (1) After the heat preservation is completed, put the TB17 titanium alloy blank into the mold for isothermal forging, the deformation of the blank is controlled at 18%, the deformation rate of the blank is controlled at 0.35mm / s, and the temperature of the isothermal forging mold is set at 876 ℃;

[0023] (3) Step (2) After the forging is completed, the billet is taken out and cooled to room temperature at a cooling rate of 5.5°C / s.

[0024] After carrying out s...

Embodiment 2

[0026] This embodiment is for forging a nearly β-type TB17 titanium alloy forging with a phase transition point of 843°C.

[0027] The specific implementation process is as follows:

[0028] (1) Put the TB17 titanium alloy billet into the effective working area of ​​the resistance furnace that has reached the set heating temperature of 800°C for heating and heat preservation. The heat preservation time is 72 minutes, and then the temperature is raised to 870°C with the furnace, and then heat preservation is carried out for 36 minutes;

[0029] (2) Step (1) After the heat preservation is completed, put the TB17 titanium alloy blank into the mold for isothermal forging, the deformation of the blank is controlled at 23%, the deformation rate of the blank is controlled at 0.65mm / s, and the temperature of the isothermal forging mold is set at 870 ℃;

[0030] (3) Step (2) After the forging is completed, the billet is taken out and cooled to room temperature at a cooling rate of 2.5...

Embodiment 3

[0033] This embodiment is for forging a nearly β-type TB17 titanium alloy forging with a phase transition point of 843°C.

[0034] The specific implementation process is as follows:

[0035] (1) Put the TB17 titanium alloy billet into the effective working area of ​​the resistance furnace that has reached the set heating temperature of 813°C for heating and heat preservation. The heat preservation time is 64 minutes, and then the temperature is raised to 858°C with the furnace, and then heat preservation is carried out for 32 minutes;

[0036] (2) Step (1) After the heat preservation is completed, put the TB17 titanium alloy blank into the mold for isothermal forging, the deformation of the blank is controlled at 15%, the deformation rate of the blank is controlled at 0.4mm / s, and the temperature of the isothermal forging mold is set at 860 ℃;

[0037] (3) Step (2) After the forging is completed, the billet is taken out and cooled to room temperature at a cooling rate of 1.1°...

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Abstract

The invention discloses an isothermal forging process of a TB17 titanium alloy, and belongs to the technical field of material science. The method mainly comprises the steps that (1) a titanium alloy blank is placed in an effective working area of a resistance furnace with the set heating temperature being 785-815 DEG C for heating and heat preservation, the heat preservation time is 45-125 min, and then the titanium alloy blank is heated to 850-890 DEG C along with the furnace and then subjected to heat preservation for 25-60 min; (2) after heat preservation in the step (1) is finished, a titanium alloy blank is put into a die to be subjected to isothermal forging, the deformation amount of the blank is controlled to range from 10% to 29%, and the deformation rate of the blank is controlled to range from 0.3 mm / s to 1.25 mm / s; and (3) after forging in the step (2) is completed, the blank is taken out and cooled to the room temperature at the cooling speed of 0.5 DEG C / s-35 DEG C / s. The comprehensive mechanical property of the titanium alloy forge piece treated by the isothermal forging process can be remarkably improved, and the tensile strength and fracture toughness of the forge piece are improved.

Description

technical field [0001] The invention belongs to the technical field of material science and relates to an isothermal forging method for improving TB17 titanium alloy. Background technique [0002] The strength level of titanium alloys can reach an ultra-high strength level above 1200MPa, but it is difficult to match the comprehensive properties of strong plasticity, toughness and damage tolerance performance, which has always been the bottleneck restricting the development and application of ultra-high-strength titanium alloys. One of the hot research directions of strength titanium alloy. Studies have shown that β-type titanium alloys are most suitable for the development and development of high-strength and ultra-high-strength titanium alloys due to their excellent heat treatment strengthening effect, high hardenability, and good processing performance. [0003] Foreign countries have begun to develop β-type titanium alloys since the early 1940s. The first commercial β-t...

Claims

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Application Information

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IPC IPC(8): B21J5/02B21J1/06C22F1/18
CPCB21J5/02B21J1/06C22F1/183
Inventor 朱知寿王新南李明兵商国强祝力伟李静
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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