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2.3 GPa strength grade Co-Ni-Cr-based alloy and preparation method thereof

A technology of co-ni-cr and base alloy, which is applied in the field of ultra-high-strength and toughness nickel-chromium-based superalloy materials and its preparation, can solve problems such as limitations, and achieve good mechanical properties, low investment, and simple preparation process

Active Publication Date: 2021-10-15
SHENYANG AEROSPACE UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Multiphase cobalt-based MP series alloys mainly rely on the formation of martensite sheets during the deformation process to achieve strengthening and toughness, and there is a significant trade-off effect between "toughness-strength". Therefore, The ability to increase strength while maintaining a certain degree of plasticity is limited

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] Formulated as Co 44.36 Ni 32.89 Cr 19 W 1 Mo 2 V 0.5 C 0.25 (mass.%) alloy, smelted into 18Kg ingot by vacuum induction furnace, subjected to homogenization treatment at 1200℃ / 12h, processed into sheets or rods that can be processed by cold deformation, and then solid solution at 1200℃ / 2h deal with. Then carry out cold deformation (rolling, swaging, etc.) with a deformation amount of 80% to prepare corresponding sheets and rods. After aging heat treatment at 500°C / 2h and air cooling, the finished alloy is obtained.

[0025] at room temperature with 10 -3 the s -1 The tensile rate of the obtained alloy is stretched, the nominal tensile plasticity can reach more than 8%, and the yield strength can reach 2.38GPa; under the condition of liquid nitrogen, the nominal tensile plasticity can reach more than 10%, and the yield strength can reach 2.75GPa .

Embodiment 2

[0027] Formulated as Co 44.36 Ni 32.89 Cr 19 W 1 Mo 2 V 0.5 C 0.25 (mass.%) alloy, smelted into 18Kg ingot by vacuum induction furnace, subjected to homogenization treatment at 1150℃ / 12h, processed into sheets or rods that can be processed by cold deformation, and then solid solution at 1150℃ / 2h deal with. Then carry out cold deformation (rolling, swaging, etc.) with a deformation amount of 80% to prepare corresponding sheets and rods. After aging heat treatment at 500°C / 3h and air cooling, the finished alloy is obtained.

[0028] at room temperature with 10 -3 the s -1 The tensile rate of the obtained alloy is stretched, the nominal tensile plasticity can reach more than 8%, and the yield strength can reach 2.33GPa; under the condition of liquid nitrogen, the nominal tensile plasticity can reach more than 10%, and the yield strength can reach 2.72GPa . .

Embodiment 3

[0030] Formulated as Co 44.36 Ni 32.89 Cr 19 W 1 Mo 2 V 0.5 C 0.25 (mass.%) alloy, smelted into 18Kg ingot by vacuum induction furnace, subjected to homogenization treatment at 1200℃ / 12h, processed into sheets or rods that can be processed by cold deformation, and then solid solution at 1200℃ / 2h deal with. Then carry out cold deformation (rolling, swaging, etc.) with a deformation amount of 80% to prepare corresponding sheets and rods. After aging heat treatment at 500°C / 4h and air cooling, the finished alloy is obtained.

[0031] at room temperature with 10 -3 the s -1 The tensile rate of the obtained alloy is stretched, the nominal tensile plasticity can reach more than 8%, and the yield strength can reach 2.30GPa; under the condition of liquid nitrogen, the nominal tensile plasticity can reach more than 10%, and the yield strength can reach 2.70GPa .

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Abstract

The invention discloses a 2.3 GPa strength grade Co-Ni-Cr-based alloy and a preparation method thereof. The alloy comprises the following components of, in percentage by mass, 42%-45% of Co, 30%-33% of Ni, 18%-21% of Cr, 0.8%-1.2% of W, 1.8%-2.2% of Mo, 0.3%-0.7% of V and 0.15%-0.3% of C. The preparation method of the alloy comprises the steps of casting, homogenization treatment, solution treatment, cold deformation treatment and aging heat treatment. The tensile strength of the alloy can reach 2.30 GPa or above, the alloy has certain plasticity, the preparation process is simple, and the alloy can be produced through conventional casting and cold and hot machining processes.

Description

technical field [0001] The invention belongs to the field of preparation of cobalt-chromium-nickel-based alloy materials, and relates to ultra-high-strength toughness deformation structural materials, especially ultra-high-strength toughness nickel-chromium-based superalloy materials used in aerospace and other fields and a preparation method thereof. Background technique [0002] Fasteners are key components that carry high stress in mechanical power transmission structures. The materials used to prepare fasteners first require excellent comprehensive properties that match high strength and high toughness. Before the mid-1970s, the standard fasteners used in aerospace used H-11 alloy (AMS6408), which is a variant of hot work die steel. 8%), it has a tensile strength greater than 1500MPa, and the highest strength level can reach 1800MPa, which meets the performance requirements of fasteners in aerospace and other fields at that time. However, this series of alloys has poor ...

Claims

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Application Information

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IPC IPC(8): C22C30/00C22C1/02C22F1/16
CPCC22C30/00C22C1/02C22F1/16
Inventor 杜兴蒿金城炎闫霏史传鑫盖业辉段国升张利武保林王大鹏邹乃夫张璐东野生栓
Owner SHENYANG AEROSPACE UNIVERSITY
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