Manufacturing method of TC4 titanium alloy ring for aero-engine outer duct

A technology of aero-engine and manufacturing method, which is applied in the field of manufacturing of TC4 titanium alloy rings for aero-engine outer ducts, can solve the problems of low utilization rate of forging raw materials, and achieves reduction of machining time, improvement of material utilization, and reduction of machining amount of effect

Inactive Publication Date: 2013-12-25
GUIZHOU AVIATION TECHN DEV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a method for manufacturing a TC4 titanium alloy ring for an aero-engine external duct, which solves the problem of low forging raw material utilization of the TC4 titanium alloy ring for an aero-engine external duct in the prior art

Method used

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  • Manufacturing method of TC4 titanium alloy ring for aero-engine outer duct
  • Manufacturing method of TC4 titanium alloy ring for aero-engine outer duct
  • Manufacturing method of TC4 titanium alloy ring for aero-engine outer duct

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0045] (1) Cutting and heating:

[0046] The TC4 titanium alloy blank is rounded to R20, heated to the deformation temperature of 30°C below the phase transition point, and the holding time is calculated as 6min / 10mm;

[0047] (2) The first fire upsetting and punching:

[0048] Upsetting the TC4 titanium alloy billet in step (1) to a deformation of 30%, punching with a punch until the hole diameter is 55% of the outer diameter, the upsetting and punching are completed in the first fire, and the final forging temperature is ≥850°C;

[0049] (3) Second fire heating, saddle reaming:

[0050] Carry out the second fire heating to heat the punched blank to the deformation temperature of 30°C below the phase transition point, heat and keep it warm, the time is calculated according to 6min / 10mm, and the diameter of the small hole is 75% of the small hole outer diameter %, the diameter of the large hole is 80% of the outer diameter of the large hole, the final forging temperature is ...

Embodiment 2

[0056] (1) Cutting and heating:

[0057] The TC4 titanium alloy blank is rounded to R20, heated to the deformation temperature of 50°C below the phase transition point, and the holding time is calculated as 6min / 10mm;

[0058] (2) The first fire upsetting and punching:

[0059] Upsetting the TC4 titanium alloy billet in step (1) to a deformation of 40%, punching with a punch until the hole diameter is 65% of the outer diameter, the upsetting and punching are completed in the first fire, and the final forging temperature is ≥850°C;

[0060] (3) Second fire heating, saddle reaming:

[0061]Carry out the second fire heating to heat the punched blank to the deformation temperature of 50°C below the phase transition point, heat and keep it warm, and the time is calculated according to 6min / 10mm. %, the diameter of the large hole is 85% of the outer diameter of the large hole, the final forging temperature is ≥850°C, return to the furnace while it is hot, the heating time is calcu...

Embodiment 3

[0067] (1) Cutting and heating:

[0068] The TC4 titanium alloy blank is rounded to R20, heated to the deformation temperature of 40°C below the phase transition point, and the holding time is calculated as 6min / 10mm;

[0069] (2) The first fire upsetting and punching:

[0070] Upsetting the TC4 titanium alloy billet in step (1) to a deformation of 35%, punching with a punch until the hole diameter is 60% of the outer diameter, the upsetting and punching are completed in the first fire, and the final forging temperature is ≥850°C;

[0071] (3) Second fire heating, saddle reaming:

[0072] Carry out the second fire heating to heat the punched blank to the deformation temperature of 40°C below the phase transition point, heat and keep it warm, the time is calculated according to 6min / 10mm, and the hole diameter of the small hole is 77.5% of the small hole outer diameter %, the diameter of the large hole is 82.5% of the outer diameter of the large hole, the final forging temper...

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Abstract

The invention discloses a manufacturing method of a TC4 titanium alloy ring for an aero-engine outer duct. The method comprises the following steps: rounding a TC4 titanium alloy blank to form a fillet R20; heating to a deformation temperature which is 30-50 DEG C below a phase transformation point; determining the heat-preserving time by 6 minutes per 10 millimeters; performing primary upsetting and punching and secondary heating, mandrel supporter broaching and final rolling; and annealing, preserving heat at 715-725 DEG C for 85-95 minutes, and performing air cooling treatment. According to the method, special-shaped rings of similar shapes are adopted, so that the machining amount is reduced, the material utilization ratio is increased, and the machining time is shortened; meanwhile, an original streamline is better protected, and the product has more excellent performance.

Description

technical field [0001] The invention relates to a method for manufacturing a TC4 titanium alloy ring for an aeroengine external duct. Background technique [0002] TC4 titanium alloy has a series of advantages such as excellent corrosion resistance, small density, high specific strength, good toughness and weldability, and has been successfully applied in aerospace, petrochemical, shipbuilding, automobile, pharmaceutical and other departments . For ordinary TC4 titanium alloy forgings, the production process in the prior art is relatively mature, while the TC4 titanium alloy anisotropic ring forgings for aerospace engine external ducts have high quality requirements, strict performance index requirements, and relatively complicated forging processes. [0003] At present, the forging of TC4 titanium alloy rings for aero-engine external ducts usually adopts rectangular rings. Although the production of rectangular rings is simpler and the process is more mature, because the o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00
Inventor 谢撰业吴永安杨家典王治武张园园
Owner GUIZHOU AVIATION TECHN DEV
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