Near-isothermal forging formation method for TC4 titanium alloy hollow shaft neck forged piece

A hollow journal and isothermal forging technology, which is applied in the field of warm forging and forming, can solve the problems of small deformation of the rod, uneven deformation, and affecting the quality of forgings, and achieve the effect of preventing temperature rise and increasing deformation

Inactive Publication Date: 2017-04-26
GUIZHOU ANDA AVIATION FORGING
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Problems solved by technology

Since the forging is a key rotating part of an aircraft engine, the working conditions are very harsh, and the forging is required to have high strength, fracture toughness, and good low-cycle fatigue performance. It is difficult to meet these performance requirements by ordinary die forging and free forging.
At present, this type of forging is mainly formed by closed die forging of billets, and then produced by machining an

Method used

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  • Near-isothermal forging formation method for TC4 titanium alloy hollow shaft neck forged piece
  • Near-isothermal forging formation method for TC4 titanium alloy hollow shaft neck forged piece
  • Near-isothermal forging formation method for TC4 titanium alloy hollow shaft neck forged piece

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[0015] To implement the near isothermal forging forming method of the TC4 titanium alloy hollow journal forgings of the present invention, it is necessary to provide forging heating furnaces, presses, manipulators and other equipment. The specific implementation:

[0016] The main chemical element content (weight percentage) of the TC4 alloy is: Al content 5.5%~6.8%, V content 3.5%~4.5%, Fe content 0.30%, C content 0.10%, N content 0.05%, The H content is 0.015%, O content is 0.20%, and the balance is Ti.

[0017] The steps of this method are as follows:

[0018] Heat the TC4 titanium alloy bar material according to the specifications in the forging heating furnace, first heat the bar material to 40℃ below the phase transition point for heat preservation, and calculate the heat preservation time according to 0.3min / mm~0.5min / mm; then heat up to phase Heat preservation at 30℃ above the change point, and the heat preservation time is calculated as 0.4min / mm~0.6min / mm; after heat pres...

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Abstract

The invention discloses a near-isothermal forging formation method for a TC4 titanium alloy hollow shaft neck forged piece. The method includes the steps that after a TC4 titanium alloy bar is heated according to a certain mode, upsetting, punching, pre-rolling and chamfering are performed to obtain a rectangular ring billet; and then the rectangular ring billet is placed into a forming die to be formed at a certain deformation speed, and accordingly the TC4 titanium alloy hollow shaft neck forged piece is obtained. By the adoption of the method, the deformation amounts of all regions can be reasonably distributed, so that the optimum matching structure property is achieved. The near-isothermal forging formation method is used for extrusion forming of the hollow shaft neck forged piece.

Description

technical field [0001] The invention relates to a near-isothermal forging forming method, in particular to a near-isothermal forging forming method for a TC4 titanium alloy hollow journal forging. Background technique [0002] TC4 titanium alloy hollow journal forgings are hollow thin-walled special-shaped parts. The upper end of the shape is a large bell mouth, and the lower end has a cylindrical cylinder. The wall of the bell mouth is thin, and the diameter is large, and the wall thickness of the cylinder is thin. Since the forging is a key rotating part of an aircraft engine, the working conditions are very harsh, and the forging is required to have high strength, fracture toughness, and good low-cycle fatigue performance. It is difficult to meet these performance requirements by ordinary die forging and free forging. At present, this type of forging is mainly formed by closed die forging of billets, and then produced by machining and digging. However, on the one hand, th...

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Application Information

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IPC IPC(8): B21K1/06B21K29/00B21J5/02
CPCB21K1/06B21J5/02B21K29/00
Inventor 夏春林陈明郝晓霞杨文宇袁明涛
Owner GUIZHOU ANDA AVIATION FORGING
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