Forging and rolling integrated manufacturing process of large-diameter ultrahigh-strength high temperature resisting magnesium alloy shell part

A preparation process and ultra-high-strength technology, which is applied in the deformation of magnesium alloys, forging deformation and ring rolling deformation of Mg-Gd-Y-Zr rare earth magnesium alloys, and can solve the problems of difficult preparation of magnesium alloy shell parts and limitation of continuous deformation, etc. problem, to achieve the effect of uniform deformation and small anisotropy

Active Publication Date: 2017-08-04
CENT SOUTH UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Moreover, the special hexagonal close-packed structure of magnesium alloy makes it easy to produce strong texture during deformation, which limits its

Method used

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  • Forging and rolling integrated manufacturing process of large-diameter ultrahigh-strength high temperature resisting magnesium alloy shell part
  • Forging and rolling integrated manufacturing process of large-diameter ultrahigh-strength high temperature resisting magnesium alloy shell part
  • Forging and rolling integrated manufacturing process of large-diameter ultrahigh-strength high temperature resisting magnesium alloy shell part

Examples

Experimental program
Comparison scheme
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Example Embodiment

[0024] Example 1

[0025] First, semi-continuous electromagnetic casting is used to prepare an ingot with a diameter of φ400mm and a length of 2500mm, with a composition of Mg-9.20Gd-2.90Y-0.20Ag-0.05Er-0.39Zr (wt.%). After the casting is completed, it is annealed at 225℃ for 14h. , The ingots with a diameter of φ380mm and a length of 800mm were machined out, and the temperature was kept at 520℃ for 15h for homogenization annealing. The ingot is forged and billeted. Before forging, the ingot is kept at 490°C for 10 hours. The upper and lower anvils are heated to 350°C, and the ingot is forged and deformed at a slow speed of 10mm / s on a vertical hydraulic press. The specific process is: Take the height direction of the cylindrical blank and the two arbitrarily vertical radial directions respectively as the Z, Y and X directions; first, perform 6 passes along the Z, Y and X directions, the pass deformation is 30%, and the cylindrical The blank is pressed into a hexahedron; then, u...

Example Embodiment

[0026] Example 2

[0027] First, semi-continuous electromagnetic casting is used to prepare ingots with a diameter of φ450mm and a length of 2500mm with a composition of Mg-8.92Gd-2.23Y-0.28Ag-0.12Er-0.36Zr (wt.%), such as figure 1 As shown, the stress-relieving annealing is kept at 200°C for 16 hours, and an ingot with a diameter of φ420mm and a length of 1075mm is machined out, and the ingot is subjected to homogenization annealing at 490°C for 20 hours. The ingot is forged and billeted. Before forging, the ingot is kept at 520°C for 10 hours, the upper and lower flat anvils are heated to 325°C, and the forging deformation is carried out at a slow speed of 6mm / s on a vertical hydraulic press. The specific process is as follows: The height direction of the blank and the two arbitrarily vertical radial directions are respectively the Z, Y and X directions; firstly, the upsetting is carried out 3 passes along the Z, Y and X directions with a pass deformation of 40%, and the cylindr...

Example Embodiment

[0028] Example 3

[0029] First, semi-continuous electromagnetic casting is used to prepare ingots with a diameter of φ450mm and a length of 2500mm, with a composition of Mg-8.71Gd-2.64Y-0.25Ag-0.12Er-0.35Zr(wt.%), and heat-relief annealing at 250℃ for 14h, and mechanical processing An ingot with a diameter of φ420mm and a length of 1075mm is produced and homogenized and annealed at 500℃ for 15h. The ingot is forged and billeted. Before forging, the ingot is kept at 510°C for 12h, the upper and lower anvils are heated to 300°C, and then 8mm / s slow multi-directional forging is performed on a vertical hydraulic press. The specific process is as follows: The two radial directions in the height direction and any vertical direction of the shaped blank are respectively Z, Y and X directions; firstly, the upsetting is carried out 4 passes along the Z, Y and X directions, with a pass deformation of 35%, and the cylindrical blank is pressed Turn into a hexahedron; then use Y or X as the ...

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Abstract

The invention discloses a forging and rolling integrated manufacturing process of a large-diameter ultrahigh-strength high temperature resisting magnesium alloy shell part. The manufacturing process comprises the following steps in sequence: semi-continuous electromagnetic casting; machining of an ingot blank; uniform annealing; multi-directional free forging; mechanical perforation; annular rolling; and T6 thermal treatment. The dimension of the prepared shell part is as follows: the outer diameter Phi is 600 mm to 1700 mm; the wall thickness is 35 mm to 100 mm; the height is 300 mm to 700 mm; the T6-state room-temperature tangential and height-direction tensile strength is larger than or equal to 470 MPa; the elongation rate is larger than or equal to 5%; the tangential and height-direction tensile strength at the temperature of 200 DEG C is larger than or equal to 350 MPa; and the elongation rate at the temperature of 200 DEG C is larger than or equal to 7%. A product prepared by the process disclosed by the invention has the characteristics of large size, no cracks, ultrahigh room-temperature strength, excellent heat resistance and the like, and the process disclosed by the invention can provide a qualified magnesium alloy shell part for the fields such as aeronautics and astronautics.

Description

technical field [0001] The invention relates to the field of magnesium alloy deformation, in particular to the field of forging deformation and ring rolling deformation of Mg-Gd-Y-Zr rare earth magnesium alloy. [0002] technical background [0003] As an important structural part in the aerospace field, large-diameter shell parts are generally made of aluminum alloy. However, in view of the urgent need for weight reduction in the above-mentioned fields, replacing some aluminum shell parts with magnesium alloys with lower density is of great significance for reducing fuel consumption and improving the speed and flight distance of aircraft. However, it is difficult to prepare shell parts with qualified performance by using magnesium alloy. The special working environment of the aircraft requires that the mechanical properties of the structural parts meet the standards and the heat resistance is good. However, traditional magnesium alloys that have been developed more maturel...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00B64C1/00B64C2001/0081
Inventor 刘楚明王必正高永浩蒋树农万迎春王俊凯
Owner CENT SOUTH UNIV
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