Method for manufacturing TC25 titanium alloy ring piece

A manufacturing method, titanium alloy technology, applied in the direction of metal rolling, etc., can solve the problems of low tensile strength, 500 ℃ high tensile performance difficult to meet the standard requirements, etc., to achieve the effect of improving mechanical properties

Active Publication Date: 2014-01-22
GUIZHOU AVIATION TECHN DEV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patented technology allows for better strengthening by reducing strain on forgings made from materials like titanium or tantalum due to their unique crystal structure called beta". By performing this process at different temperatures over several hours before finalizing it, these techniques improve its overall quality while maintaining good physical characteristics such as tensile elongation (tensility) and toughness.

Problems solved by technology

This patented technical problem addressed in this patents relates to improving the mechanical property (tensility) and durability of Titanum alloys during processing such as hot press formation or mill pressing processes without compromising their quality.

Method used

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  • Method for manufacturing TC25 titanium alloy ring piece
  • Method for manufacturing TC25 titanium alloy ring piece
  • Method for manufacturing TC25 titanium alloy ring piece

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0050] (1) Cutting, heating, upsetting and punching of pre-rolled slabs:

[0051] Heat the TC25 titanium alloy pre-rolled billet to the deformation temperature of 30°C under the phase transition point, 6min / 10mm, deform it by 50% by upsetting to obtain a solid cylinder, punch the solid cylinder so that the inner diameter of the hole is 60 of the outer diameter After %, a hollow cylinder is obtained, upsetting and punching are completed in one fire, and the final forging temperature is ≥850°C;

[0052] (2) Horse frame reaming:

[0053]Ream the hollow cylinder described in step (1) through the horse frame so that the inner diameter of the hole is 70% of the outer diameter, and the final forging temperature is ≥850°C, and return to the furnace while it is hot. time halved;

[0054] (3) Final rolling:

[0055] The forging obtained in step (2) is subjected to final rolling so that the inner diameter of the hole is 85% of the outer diameter, and the final forging temperature is ≥...

Embodiment 2

[0059] (1) Cutting, heating, upsetting and punching of pre-rolled slabs:

[0060] Heat the TC25 titanium alloy pre-rolled billet to the deformation temperature of 50°C under the phase transition point, 6min / 10mm, deform it by 60% by upsetting to obtain a solid cylinder, and punch the solid cylinder so that the inner diameter of the hole is 70% of the outer diameter After %, a hollow cylinder is obtained, upsetting and punching are completed in one fire, and the final forging temperature is ≥850°C;

[0061] (2) Horse frame reaming:

[0062] Ream the hollow cylinder described in step (1) through the horse frame so that the inner diameter of the hole is 75% of the outer diameter, and the final forging temperature is ≥850°C, and return it to the furnace while it is hot. The time is calculated according to the actual thickness at 6min / 10mm. time halved;

[0063] (3) Final rolling:

[0064] The forging obtained in step (2) is subjected to final rolling so that the inner diameter ...

Embodiment 3

[0068] (1) Cutting, heating, upsetting and punching of pre-rolled slabs:

[0069] Heat the TC25 titanium alloy pre-rolled billet to the deformation temperature of 50°C under the phase transition point, 6min / 10mm, deform it by 60% by upsetting to obtain a solid cylinder, and punch the solid cylinder so that the inner diameter of the hole is 70% of the outer diameter After %, a hollow cylinder is obtained, upsetting and punching are completed in one fire, and the final forging temperature is ≥850°C;

[0070] (2) Horse frame reaming:

[0071] Ream the hollow cylinder described in step (1) through the horse frame so that the inner diameter of the hole is 72.5% of the outer diameter, and the final forging temperature is ≥850°C, and return to the furnace while it is hot. The time is calculated as 6min / 10mm according to the actual thickness. time halved;

[0072] (3) Final rolling:

[0073] The forging obtained in step (2) is subjected to final rolling so that the inner diameter o...

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Abstract

The invention discloses a method for manufacturing a TC25 titanium alloy ring piece. A TC25 titanium alloy pre-rolled compact is heated to the deformation temperature of 30-50 DEG C below a phase transformation point, upsetting is carried out to enable the TC25 titanium alloy pre-rolled compact to be deformed by 50%-60% to obtain a solid cylinder, punching is carried out on the solid cylinder to enable the size of the inner diameter of the hole of the solid cylinder to be 60%-70% of the size of the outer diameter of the hole of the solid cylinder, a hollow cylinder is obtained, then mandrel supporter hole broadening is carried out, the size of the inner diameter of the hole of the hollow cylinder is made to be 70%-75% of the size of the outer diameter of the hole, a final forging temperature>=850 DEG C, the hollow cylinder is melted down when the hollow cylinder is hot, and heat preservation time is halved as is calculated with an actual thickness of 6min/10mm. Final rolling is carried out, the size of the inner diameter of the hole of the hollow cylinder is made to be 85%-90% of the size of the outer diameter of the hole, and a final rolling temperature >=850 DEG C. At last, double annealing processing is carried out, and the TC25 titanium alloy ring piece is obtained. The reasonable deformation temperature is adopted, and forging is facilitated. Air cooling is adopted after the forging, cooling is accelerated, the cooling process of air cooling is adopted in the double annealing process, and the mechanical performance of a forge piece is greatly improved.

Description

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Claims

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Application Information

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Owner GUIZHOU AVIATION TECHN DEV
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