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High-temperature alloy and preparation method thereof

A technology for superalloys and alloy ingots, applied in the field of metal structural materials, can solve the problems of research and reports of superalloys without nano-twins, loss of strengthening effect, etc., and achieve good twinning deformation ability, stacking fault energy reduction, and simple method. Effect

Active Publication Date: 2020-12-15
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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Problems solved by technology

However, this strengthening theory is only applicable to room temperature environment, and at high temperature, due to the easy growth of nano twins, this strengthening effect is lost.
[0008] The inventors of the present invention have found that there is no relevant research and report on superalloys containing nano-twins in the prior art

Method used

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  • High-temperature alloy and preparation method thereof

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preparation example Construction

[0039] The invention provides a high-temperature alloy and a preparation method thereof. The high-temperature alloy contains nano-twins. Due to the strengthening effect of the nano-twins, the high-temperature alloy has excellent high-temperature strength, and is mainly suitable for high temperature and high stress (700-850° C.) Used components such as turbine disks and blades for aero-engines.

[0040] On the one hand, the composition design of the superalloy containing nano-twins of the present invention is as follows: by weight percentage, the superalloy includes the following composition: Co 18-25%, Cr 11-15%, Ti 5-6.3%, Al 1.0-3.0%, W 1-4%, Mo1-4%, Fe 0-4% (preferably 2.1-4%), Ta 0-4% (preferably 1-4%), C<0.05% (preferably at 0.02 -0.05%), Zr<0.05% (preferably 0.02-0.05%), and the balance is Ni. The sum of the weight percentages of Co and Ta is controlled between 20-29 wt%.

[0041] Here, it should be noted that: the role of alloying elements in the superalloy of the pre...

Embodiment 1

[0064] Embodiment 1 Design a superalloy, wherein, by weight percentage, the chemical composition of the superalloy is: Co23%, Cr 14%, Ti 5.8%, Al 2.4%, W 1.5%, Mo 3%, Fe 2.5% , C 0.02%, Zr 0.03%, and the balance is Ni.

[0065] Wherein, the preparation method of the superalloy comprises the following steps:

[0066]1): The alloy raw material is put into a vacuum induction furnace for melting, and the melted alloy liquid is poured into electrode rods; then, the electrode rods are remelted by electroslag and cast into alloy ingots.

[0067] 2): Treat the alloy ingot at 1130°C-1150°C for 10 hours, and then at 1170-1200°C for 10 hours.

[0068] 3): The homogenized alloy ingot is subjected to hot extrusion treatment at a temperature of 1120° C. to 1150° C. to prepare an alloy rod with a grain size of 30 μm. The melting point Tm of the alloy rod is 1345°C.

[0069] 4): Cut a part from the alloy rod as a workpiece. Seven parts were cut to obtain seven processed parts, and the fol...

Embodiment 2

[0078] Embodiment 2 Design a superalloy, wherein, by weight percentage, the chemical composition of the superalloy is: Co19%, Cr 13%, Ti 5.5%, Al 2.5%, W 1.5%, Mo 3%, Ta 2% , C 0.02%, Zr 0.03%, and the balance is Ni.

[0079] Wherein, the preparation method of the superalloy comprises the following steps:

[0080] 1) The alloy raw material is put into a vacuum induction furnace for smelting, and the smelted alloy liquid is poured into an electrode rod; then, the electrode rod is remelted by electroslag, and then poured into an alloy ingot.

[0081] 2) Treat the alloy ingot at 1130°C-1150°C for 10 hours, and then at 1170-1200°C for 10 hours.

[0082] 3) The homogenized alloy ingot is hot-extruded between 1110° C. and 1140° C. to prepare an alloy rod with a grain size of 30 μm. The melting point Tm of the alloy rod is 1347°C.

[0083] 4) Cut a part from the alloy rod as a workpiece. Cut 7 parts to obtain 7 workpieces. These 7 workpieces are processed by 7 different processes...

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Abstract

The invention provides a high-temperature alloy and a preparation method thereof. The high-temperature alloy contains nano twin crystals, and comprises the following components in percentage by weight: 18-25% of Co, 11-15% of Cr, 5-6.3% of Ti, 1.0-3.0% of Al, 1-4% of W, 1-4% of Mo, 0-4% of Fe, 0-4% of Ta, less than 0.05% of C, less than 0.05% of Zr and the balance of Ni. The preparation method ofthe high-temperature alloy comprises the following steps that (1) alloy raw materials are smelted and subjected to pouring to form an electrode; and the electrode is subjected to electroslag remeltingtreatment, and an alloy ingot is formed by pouring; 2) the alloy ingot is subjected to homogenization treatment; 3) the alloy ingot after being subjected to the homogenization treatment is subjectedto hot working treatment to obtain an alloy bar; and (4) a part cut from the alloy bar is used as a machined part, under the conditions that the temperature is 0.45-0.67 Tm and the strain rate is lower than 10<-2>s<-1>, the machined part is subjected to plastic deformation with the deformation amount being 2-30%, and the high-temperature alloy containing the nano twin crystals is obtained. The high-temperature alloy has good thermal stability at 750 DEG C or below, and the yield strength of the high-temperature alloy at 600 DEG C or below is improved by 15% or above compared with that of a high-temperature alloy without the nano twin crystals.

Description

technical field [0001] The invention relates to the field of metal structural materials, in particular to a superalloy and a preparation method thereof. Background technique [0002] In order to meet the ever-increasing performance requirements of aero-engines, the gas inlet temperature of the engine has developed from 1330°C in the 1970s to 1580-1680°C in the 1990s, and further developed to 1730°C at the beginning of this century. Superalloy turbine blades and turbine disks, as the core hot-end parts of the engine, must have continuously improved temperature bearing capacity, which makes the preparation technology of superalloy blades and turbine disks one of the key technologies in the design and manufacture of modern aero-engines . In the next 5-10 years, the development of high thrust-to-weight ratio aero-engines in my country will require the production of superalloys with higher temperature-bearing capacity. [0003] As the core component for fixing the blades, conne...

Claims

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Application Information

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IPC IPC(8): C22C19/05C22F1/10
CPCC22C19/056C22F1/10
Inventor 崔传勇张瑞周亦胄孙晓峰
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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