Deformed high-temperature alloy and manufacturing method thereof

A technology for deforming high-temperature alloys and alloys, which is applied in the field of metal structural materials, can solve problems such as inability to process and decline in thermal processing performance, and achieve the effects of increasing the use temperature, improving thermal processing performance, and good thermal processing performance

Active Publication Date: 2021-01-15
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Using traditional strengthening methods, the strengthening and machinability of superalloys for turbine discs will have an "inverted" relationship, that is, with the increase in the use temperature of superalloys, their hot workability will decrease significantly, and even cannot be achieved by casting / forging processes. processing

Method used

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  • Deformed high-temperature alloy and manufacturing method thereof
  • Deformed high-temperature alloy and manufacturing method thereof
  • Deformed high-temperature alloy and manufacturing method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0065] Embodiment 1 Design a deformed superalloy, wherein, by weight percentage, the chemical composition of the deformed superalloy is: Co 25.8%, Cr 10.4%, Ti 5.2%, Al 2.1%, W 4.2%, Mo 2.5%, C 0.02%, Zr 0.03%, the balance being Ni.

[0066] Wherein, the preparation steps of the deformed superalloy are as follows:

[0067] 1): Add alloy raw materials into a vacuum induction furnace for smelting treatment, pour the smelted alloy solution into an alloy ingot (master alloy) whose chemical composition meets the above design requirements and has no obvious casting defects.

[0068] 2): The alloy ingot is treated at a temperature range of 1130-1150°C for 25 hours, and then at a temperature range of 1170-1200°C for 26 hours.

[0069] 3): Hot forging the homogenized alloy ingot at a temperature between 1100-1150°C to prepare a deformed superalloy (that is, a deformed superalloy rod).

Embodiment 2

[0071] Embodiment 2 Design a deformed superalloy, wherein, by weight percentage, the chemical composition of the deformed superalloy is: Co 20%, Cr 9%, Ti 5.6%, Al 2.5%, W 4.7%, Mo 2.7%, Ta 4%, C 0.02%, Zr 0.03%, and the balance is Ni.

[0072] Wherein, the preparation steps of the deformed superalloy are as follows:

[0073] 1): Add alloy raw materials into a vacuum induction furnace for smelting treatment, pour the smelted alloy solution into an alloy ingot (master alloy) whose chemical composition meets the above design requirements and has no obvious casting defects.

[0074] 2): The alloy ingot is treated at a temperature range of 1130-1150°C for 25 hours, and then at a temperature range of 1170-1200°C for 26 hours.

[0075] 3): Hot forging the homogenized alloy ingot at a temperature between 1100-1150°C to prepare a deformed superalloy (that is, a deformed superalloy rod).

Embodiment 3

[0077]Embodiment 3 A deformed superalloy is designed, wherein, by weight percentage, the chemical composition of the deformed superalloy is: Co 33%, Cr 9.7%, Ti 5.7%, Al 2.4%, W 5%, Mo 2.5%, Ta 2%, C 0.02%, Zr 0.03%, and the balance is Ni.

[0078] Wherein, the preparation steps of the deformed superalloy are as follows:

[0079] 1): Add alloy raw materials into a vacuum induction furnace for smelting treatment, pour the smelted alloy solution into an alloy ingot (master alloy) whose chemical composition meets the above design requirements and has no obvious casting defects.

[0080] 2): The alloy ingot is treated at a temperature range of 1130-1150°C for 25 hours, and then at a temperature range of 1170-1200°C for 26 hours.

[0081] 3): Hot forging the homogenized alloy ingot at a temperature between 1100-1150°C to prepare a deformed superalloy (that is, a deformed superalloy rod).

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Abstract

The invention relates to a deformed high-temperature alloy and a manufacturing method thereof, and relates to the technical field of metal structure materials. According to the mainly adopted technical scheme, the deformed high-temperature alloy comprises the following components in percentage by weight: 20-35% of Co, 8-11% of Cr, 5.2-6% of Ti, 1.8-4.0% of Al, 4-6% of W, 2-4% of Mo, 0-4% of Ta, less than 0.05% of C, less than 0.1% of Zr and the balance of Ni. The stacking fault energy of the deformed high-temperature alloy is less than 33mJ / m < 2 >; and the volume fraction of the strengtheningphase gamma' in the deformed high-temperature alloy is 40-48%. The invention is mainly used for designing the deformed high-temperature alloy which has excellent strength at a use temperature and hasgood plasticity in a hot working temperature interval; and the deformed high-temperature alloy is mainly suitable for parts used under high temperature and high stress, such as turbine discs of aero-engines.

Description

technical field [0001] The invention relates to the technical field of metal structural materials, in particular to a deformed superalloy and a preparation method thereof. Background technique [0002] The aero-engine is the most important thing in the country, and the turbine disk is the "heart" part of the aero-engine. Due to the large size of the turbine disk parts and its complex service conditions, higher and higher requirements are put forward for the design and manufacture of turbine disk alloys, which has become one of the bottleneck technologies restricting the development of aero-engines in my country. [0003] At present, the commonly used deformed superalloys for turbine discs mainly include Inconel718 alloy (containing about 15% of γ″ precipitated phase), Waspaloy alloy (containing 20% ​​of γ′ phase), GH4586 alloy (containing 29% of γ′ phase), U720Li Alloy (containing 45% γ′ phase). The design concept of these alloys is to add more solid solution strengthening ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C22C30/00C22F1/10
CPCC22C19/057C22C19/056C22C30/00C22F1/10Y02P10/25
Inventor 崔传勇张瑞孙晓峰周亦胄
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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