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

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0023] Example 1

[0024] Formulation ingredients CO 44.36 Ni 32.89 CR 19 W 1 Mo 2 V 0.5 C 0.25 (mass.%) alloy, by a vacuum induction furnace into 18kg ingot, a homogenization treatment of 1200 ° C / 12h, processed into sheet or rods that can be processed by cold-deformed processes, and then carry out 1200 ° C / 2H solid solution deal with. The corresponding sheet and a bar are then prepared for cold deformation (rolling, rotary forging processes) of the deformation amount of 80%. After 500 ° C / 2H, heat treatment, air cooling, and alloy finished products.

[0025] 10 at room temperature -3 s -1 The tensile rate is stretched with the obtained alloy finished product, and the nominal pulloplasts reached more than 8%, the yield strength can reach 2.38 GPa; under liquid nitrogen conditions, the nominal pullopathy has more than 10%, and the yield strength can reach 2.75 GPa. .

Example Embodiment

[0026] Example 2

[0027] Formulation ingredients CO 44.36 Ni 32.89 CR 19 W 1 Mo 2 V 0.5 C 0.25 (mass.%) alloy, by a vacuum induction furnace, a homogenization treatment of 1150 ° C / 12H is performed, and the sheet or bar can be processed into a cold-deformed processing, and then 1150 ° C / 2H solid solution deal with. The corresponding sheet and a bar are then prepared for cold deformation (rolling, rotary forging processes) of the deformation amount of 80%. After 500 ° C / 3H, heat treatment, air cooling, and alloy finished products.

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

Example Embodiment

[0029] Example 3

[0030] Formulation ingredients CO 44.36 Ni 32.89 CR 19 W 1 Mo 2 V 0.5 C 0.25 (mass.%) alloy, by a vacuum induction furnace into 18kg ingot, a homogenization treatment of 1200 ° C / 12h, processed into sheet or rods that can be processed by cold-deformed processes, and then carry out 1200 ° C / 2H solid solution deal with. The corresponding sheet and a bar are then prepared for cold deformation (rolling, rotary forging processes) of the deformation amount of 80%. After 500 ° C / 4H, heat treatment, air cooling, and alloy finished products.

[0031] 10 at room temperature -3 s -1 The tensile rate is stretched with the obtained alloy finished product, and the nominal pullopathy has more than 8%, the yield strength can reach 2.30 GPa; under liquid nitrogen conditions, the nominal pull-out is 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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