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Continuous combined extrusion blooming method for difficult-to-deform superalloy ingot

A high-temperature alloy and composite extrusion technology, applied in the direction of metal extrusion dies, etc., can solve the problems of low material utilization rate and production efficiency, uneven deformation structure, insufficient extrusion ratio, etc., to improve material yield and increase Uniformity and flatness of tissue, effect of reducing residual stress level

Active Publication Date: 2021-03-09
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The present invention is aimed at the deficiencies in the above-mentioned prior art and provides a continuous compound extrusion blanking method for hard-to-deform superalloy ingots. The problem of low rate and production efficiency, as well as the inhomogeneous deformation structure caused by insufficient extrusion ratio in the direct extrusion billet opening process, and the large extrusion ratio deformation is prone to cracking defects, etc. question

Method used

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  • Continuous combined extrusion blooming method for difficult-to-deform superalloy ingot
  • Continuous combined extrusion blooming method for difficult-to-deform superalloy ingot
  • Continuous combined extrusion blooming method for difficult-to-deform superalloy ingot

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Embodiment 1

[0046] Adopt the method described in the present invention to carry out the step of continuous compound extrusion blanking to GH710 alloy ingot as follows:

[0047] Step 1. Extrusion mold preparation

[0048] like figure 1 As shown, the method adopts an extrusion molding die including a punch 1, an extrusion steel pad 2, an extrusion cylinder 6, a reducing die 8, a positive extrusion die 9, a reducing die 8 and a forward extrusion die. The cooperation between the pressing die 9 and the extrusion barrel 6 is a transition fit, and is coaxial with the center line of the punch 1. The diameter reducing extrusion die 8 is composed of one insert, and the section reduction rate is designed to be 30%. Cone angle α 1 is 30°, the extrusion ratio of positive extrusion die 9 is designed to be 9:1, and the die cone angle α 2 is 160°;

[0049] Step 2. Package welding

[0050] The jacket material is made of 304 stainless steel. The unilateral gap between the inner diameter of the jacket ...

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Abstract

The invention relates to a continuous combined extrusion blooming method for a difficult-to-deform superalloy ingot. According to the method, the guidance positioning effect of a reducing extrusion female die is utilized to perform reducing extrusion, upsetting deformation and forward extrusion continuous combined extrusion one-off forming in an extrusion cylinder, so that multi-heating-number upsetting blooming in an existing process is omitted. Firstly, part of the cast structure of the difficult-to-deform superalloy ingot is broken through small-deformation reducing extrusion and upsettingdeformation, so that the difficult-to-deform superalloy ingot can generate plastic deformation which is large enough to realize recrystallized grain refinement; meanwhile, the radial constraint effectapplied to the blank by the extrusion cylinder and a cavity of the reducing extrusion female die effectively prevents buckling deformation in the upsetting process of the superalloy ingot with a large height-diameter ratio; and finally, through extrusion deformation with a large extrusion ratio (8:1-12:1), the cast structure with a thick core is fully broken, and a uniform recrystallization behavior is generated on the surface and the core of a bar, so that the uniform fine-grain superalloy bar with the grain size reaching the 7-9 level is obtained.

Description

technical field [0001] The invention relates to a method for continuous compound extrusion blanking of a hard-to-deform high-temperature alloy ingot, which belongs to the technical field of thermal processing and relates to an improvement of the blank-opening process of a hard-to-deform high-temperature alloy ingot. Background technique [0002] High-performance engine turbine disk superalloys can be divided into powder superalloys and cast-forged deformed superalloys. Foreign powder superalloys have been relatively mature, and have gradually become the main material for turbine components in high-performance aero-engines. However, compared with the conventional casting and forging process, the production process of the powder superalloy turbine disk is complicated and the production cost is high. Whether in Europe, America or Russia, while developing the powder superalloy turbine disk, they have never stopped developing high-alloyed deformed superalloy turbine disks. Disk ...

Claims

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Application Information

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IPC IPC(8): B21C23/00B21C23/22B21C25/02B21C29/00B21C23/32
CPCB21C23/002B21C23/005B21C23/22B21C25/02B21C29/003B21C23/32
Inventor 兰博陈由红林莺莺张敏聪李金栋孙兴
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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