Heat treatment process for prolonging fatigue life of GH4738 alloy

A fatigue life, nickel-based superalloy technology, applied in the field of superalloy heat treatment, can solve the problems of reducing alloy service performance, alloy crack initiation, etc., to achieve the effect of improving fatigue life, inhibiting growth, and reducing the number of carbides

Active Publication Date: 2021-12-31
UNIV OF SCI & TECH BEIJING
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compared with single crystal nickel-based superalloys, there are more interface regions in polycrystalline GH4738 alloys, and metastable interface regions (especially grain boundaries) tend to precipitate larger-sized massive carbides during heat treatment. , the alloy in service is easy to initiate cracks here, thereby reducing the service performance of the alloy, especially the thermal fatigue performance

Method used

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  • Heat treatment process for prolonging fatigue life of GH4738 alloy
  • Heat treatment process for prolonging fatigue life of GH4738 alloy
  • Heat treatment process for prolonging fatigue life of GH4738 alloy

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] The first step, raw material preparation:

[0029] The GH4738 nickel-based superalloy with the following components is selected according to the mass fraction: carbon 0.08%, chromium 19.61%, cobalt 13.55%, molybdenum 4.23%, titanium 2.98%, aluminum 1.47%, boron 0.07%, zirconium 0.11%, and the balance is nickel. Cut the alloy into Try on sticks, wash and dry until ready to use.

[0030] The second step, solution treatment:

[0031] The GH4738 alloy sample was heated to 1020°C for solution treatment at a heating rate of 25°C / min for 60 minutes, and then the alloy sample was cooled to 800°C by flowing air in the heat treatment furnace, and the cooling rate at this stage was 40°C / min; Remove and air cool to room temperature.

[0032] The third step, aging treatment:

[0033] The GH4738 alloy sample was heated to 770°C for 8 hours at a heating rate of 25°C / min, and then air-cooled to room temperature.

Embodiment 2

[0035] The first step, raw material preparation:

[0036] The GH4738 nickel-based superalloy with the following components is selected according to the mass fraction: carbon 0.08%, chromium 19.61%, cobalt 13.55%, molybdenum 4.23%, titanium 2.98%, aluminum 1.47%, boron 0.07%, zirconium 0.11%, and the balance is nickel. Cut the alloy into Try on sticks, wash and dry until ready to use.

[0037] The second step, solution treatment:

[0038] The GH4738 alloy sample was heated to 1025°C for solution treatment at a heating rate of 20°C / min for 70 minutes, and then the alloy sample was cooled to 800°C by flowing air in the heat treatment furnace, and the cooling rate at this stage was 45°C / min; Remove and air cool to room temperature.

[0039] The third step, aging treatment:

[0040] The GH4738 alloy sample was heated to 765°C for 9 hours at a heating rate of 20°C / min, and then air-cooled to room temperature.

Embodiment 3

[0042] The first step, raw material preparation:

[0043] The GH4738 nickel-based superalloy with the following components is selected according to the mass fraction: carbon 0.08%, chromium 19.61%, cobalt 13.55%, molybdenum 4.23%, titanium 2.98%, aluminum 1.47%, boron 0.07%, zirconium 0.11%, and the balance is nickel. Cut the alloy into Try on sticks, wash and dry until ready to use.

[0044] The second step, solution treatment:

[0045] The GH4738 alloy sample was heated to 1030°C for solution treatment at a heating rate of 25°C / min for 60 minutes, and then the alloy sample was cooled to 800°C by flowing air in the heat treatment furnace, and the cooling rate at this stage was 60°C / min; Remove and air cool to room temperature.

[0046] The third step, aging treatment:

[0047] The GH4738 alloy sample was heated to 760 °C for 10 h at a heating rate of 30 °C / min, and then air-cooled to room temperature.

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Abstract

The invention discloses a heat treatment process for prolonging the fatigue life of a GH4738 alloy, and belongs to the technical field of high-temperature alloy heat treatment. The process comprises the following steps that solution treatment is carried out on the GH4738 alloy under the condition that the temperature is 1000-1030 DEG C, and slow cooling and discharging air cooling are carried out in sequence; and then aging treatment is carried out at the temperature of 760-780 DEG C, and discharging air cooling is carried out to the room temperature. According to the heat treatment process, grain boundary carbide distribution in a matrix is optimized, the fatigue cycle of the alloy under the fatigue test condition is increased by 36% or above, the fatigue life of the GH4738 alloy is greatly prolonged, and then the service safety of alloy parts is improved. The heat treatment process is obvious in technical advantage and wide in market popularization prospect.

Description

technical field [0001] The invention relates to the technical field of high-temperature alloy heat treatment, more specifically, it relates to a heat treatment process for improving the fatigue life of GH4738 alloy. Background technique [0002] With the continuous development of the aviation industry, the development and research of superalloys are becoming more and more important. Superalloys (also known as heat-resistant alloys or superalloys) usually refer to metal materials that can still work normally according to the design requirements under high temperature conditions of 600-1200 °C. Anti-fatigue performance, fracture toughness, and strong oxidation resistance and thermal corrosion resistance and other comprehensive properties are widely used in the aviation field. [0003] The aero-engine is known as the "Flower of Industry", and it is one of the most technical and difficult parts in the aviation industry. In the development process of aero-engine as an aircraft ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22F1/10C22C19/05
CPCC22F1/10C22C19/055
Inventor 郑磊刘红亮赵鑫董建孟晔
Owner UNIV OF SCI & TECH BEIJING
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