Forging method of thin-wall deep cavity airplane hub die forge piece

An aircraft wheel, deep cavity technology, applied in the direction of wheels, manufacturing tools, vehicle parts, etc., can solve the problems of not involving non-complete rotationally symmetrical parts forging process research, not involving intermediate pre-forgings, etc., to achieve good deformation uniformity of forgings, The effect of preventing folding and flow-through defects and high material utilization

Active Publication Date: 2018-09-28
SHANDONG UNIV +1
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Problems solved by technology

However, the preform shape studied is only the shape of blanking cylindrical billet, which does not involve the selection of the shape of the intermediate p

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  • Forging method of thin-wall deep cavity airplane hub die forge piece
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  • Forging method of thin-wall deep cavity airplane hub die forge piece

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[0024] It should be pointed out that the following detailed descriptions are all exemplary and are intended to provide further descriptions of the application. Unless otherwise indicated, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which this application belongs.

[0025] It should be noted that the terms used here are only for describing specific embodiments, and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should also be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate There are features, steps, operations, devices, components, and / or combinations thereof.

[0026] As described in the background art, the prior art has a thin-walled deep...

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Abstract

The invention discloses a forging method of a thin-wall deep cavity airplane hub die forge piece. The forging method comprises a pre-forging method and a final forging method. According to the pre-forging method, a pre-forging die adopted in the method comprises a pre-forging upper male die and a pre-forging lower female die, the depth of the pre-forging lower female die is the same with the depthof a lower female die of a thin-wall deep cavity airplane hub final forging die, the bottom end of the pre-forging lower female die is of a boss structure drawing down from bottom to top, a round groove is formed in the lower surface of the pre-forging upper male die, an annular groove is formed in the edge of the bottom face of the round groove, an annular concave pit is arranged on the outer side of a pre-forging upper male die cavity, bottom surfaces of the annular concave pit and the annular groove are arc, the inclination angle of the outer wall of the pre-forging upper male die is the same with the inclination angle of the outer wall of the upper male die of the thin-wall deep cavity airplane hub final forging die, and the inclination angle of the inner wall of the pre-forging lowerfemale die is the same with the inclination angle of the inner wall of the lower female die of the thin-wall deep cavity airplane hub final forging die.

Description

technical field [0001] The invention relates to a forging process of an aluminum alloy aircraft hub part, in particular to a forging method of a thin-walled deep-cavity aircraft hub die forging. Background technique [0002] As the main load-bearing part of the aircraft, the wheel hub is prone to defects such as fatigue cracks when it works in a high-strength and high-load environment for a long time. Its quality plays an important role in the safety of the aircraft, so it has high requirements for its mechanical and organizational properties. . In order to reduce the weight of aircraft structural parts, aluminum alloys with high strength and light weight are currently used as materials for aircraft hub structural parts. The aircraft hub is a thin-walled deep-cavity forging with a complex structure, which is difficult to form at one time and is prone to defects such as folding, flow-through, and cracks. Adding a pre-forging process before the final forging process can make...

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Application Information

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IPC IPC(8): B21J13/02B21J5/02B21K1/40
CPCB21J5/02B21J13/02B21K1/40
Inventor 赵国群陈孝学孙璐程仁策吕正风方清万刘攀登罗顺成
Owner SHANDONG UNIV
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