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Refractory high-entropy alloy with good room-temperature plasticity and preparation method of refractory high-entropy alloy

A high-entropy alloy and refractory technology, which is applied in the field of refractory high-entropy alloy and its preparation, can solve the problems of inability to guarantee processing performance, poor room temperature plasticity, restricting the application of turbine blades, etc., so as to enhance the solid solution strengthening effect and improve the room temperature. The effect of plasticity and high temperature strength, assuring workability and performance

Pending Publication Date: 2022-06-24
西安稀有金属材料研究院有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the room temperature plasticity of most refractory high-entropy alloys is extremely poor, and the processing performance cannot be guaranteed, which seriously restricts their application in turbine blades.

Method used

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  • Refractory high-entropy alloy with good room-temperature plasticity and preparation method of refractory high-entropy alloy
  • Refractory high-entropy alloy with good room-temperature plasticity and preparation method of refractory high-entropy alloy
  • Refractory high-entropy alloy with good room-temperature plasticity and preparation method of refractory high-entropy alloy

Examples

Experimental program
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Embodiment 1

[0030] The refractory high-entropy alloy of this embodiment is denoted as V according to the molar ratio of each constituent element 24.5 Mo 15 Ta 30 Nb 30 B 0.5 .

[0031] like figure 1 As shown, the preparation method of the refractory high-entropy alloy of the present embodiment comprises the following steps:

[0032] Step 1: Prepare Mo, Ta, Nb, V and B raw materials with a quality and purity of more than 99.9%, remove the oxide scale from the surface of each raw material by grinding, and clean it with an ultrasonic cleaner, and then follow the target product refractory high entropy alloy. The molar ratio of the composition is batched;

[0033] Step 2, put the Mo, Ta, Nb metal raw materials in the raw materials prepared in the step 1 into the water-cooled copper crucible, put the V and B raw materials into the feeder, then close the smelting furnace, and vacuum the hearth of the smelting furnace to less than 2.5×10 - 3 Pa, and then filled with high-purity argon to ...

Embodiment 2

[0037] The refractory high-entropy alloy of this embodiment is denoted as V according to the molar ratio of each constituent element 24.5 Mo 15 Ta 30 Nb 30 B 0.5 .

[0038] like figure 1 As shown, the preparation method of the refractory high-entropy alloy of the present embodiment comprises the following steps:

[0039] Step 1: Prepare Mo, Ta, Nb, V and B raw materials with a quality and purity of more than 99.9%, remove the oxide scale from the surface of each raw material by grinding, and clean it with an ultrasonic cleaner, and then follow the target product refractory high entropy alloy. The molar ratio of the composition is batched;

[0040] Step 2, put the raw materials prepared in step 1 into the water-cooled copper crucible according to the order of melting point from low to high, namely V, B, Nb, Mo, Ta raw materials from bottom to top, then close the smelting furnace, and compare the smelting furnace. The furnace chamber is evacuated to less than 2.5×10 -3 P...

Embodiment 3

[0044] The refractory high-entropy alloy of this embodiment is denoted as V according to the molar ratio of each constituent element 20 Mo 10 Ta 35 Nb 34.7 B 0.3 .

[0045] The preparation method of the refractory high-entropy alloy in this example is the same as that in Example 2.

[0046] figure 2 The refractory high-entropy alloy V prepared by Examples 2 to 3 of the present invention 24.5 Mo 15 Ta 30 Nb 30 B 0.5 and V 20 Mo 10 Ta 35 Nb 34.7 B 0.3 The X-ray diffraction pattern of figure 2 It can be seen that the refractory high-entropy alloy V 24.5 Mo 15 Ta 30 Nb 30 B 0.5 and V 20 Mo 10 Ta 35 Nb 34.7 B 0.3 They are all single-phase BCC solid solution structures and belong to the category of high-entropy alloys.

[0047] image 3 The refractory high-entropy alloy V prepared by Examples 2 to 3 of the present invention 24.5 Mo 15 Ta 30 Nb 30 B 0.5 and V 20 Mo 10 Ta 35 Nb 34.7 B 0.3 The room temperature compressive stress-strain curve, from...

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Abstract

The alloy is recorded as VaMobTacNbdBe according to the molar ratio of all constituent elements, a is larger than or equal to 20 and smaller than or equal to 34, b is larger than or equal to 5 and smaller than or equal to 20, c is larger than or equal to 20 and smaller than or equal to 40, d is larger than or equal to 20 and smaller than or equal to 40, e is larger than or equal to 0.03 and smaller than or equal to 1, and a + b + c + d + e = 100; the preparation method of the alloy comprises the following steps: putting the raw materials according to a discharging sequence after burdening, and overturning and smelting for multiple times under a protective atmosphere. According to the refractory high-entropy alloy, the room-temperature plasticity and the high-temperature strength of the alloy are improved by controlling the composition elements and the molar ratio; according to the preparation method, the uniformity of all components in the alloy is improved and the loss of raw materials is reduced by controlling the discharging sequence and combining multiple times of overturning smelting, and the alloy has good room-temperature plasticity, high-temperature strength, machinability and usability and is suitable for high-temperature parts in aerospace power systems.

Description

technical field [0001] The invention belongs to the field of alloy material design and preparation, in particular to a refractory high-entropy alloy with good room temperature plasticity and a preparation method thereof. Background technique [0002] Superalloys are key materials for turbine blades in aerospace power systems. At present, the most advanced third-generation nickel-based single crystal alloy has a service temperature limit of 1150 °C, and it is difficult to further increase its service temperature. However, with the rapid development of aerospace, the performance requirements for superalloys are gradually increasing. Taking a new generation of aero-engines with a thrust-to-weight ratio of 12-15 as an example, the temperature of the front end of the turbine is designed to be between 1800°C and 2000°C. After the cooling system is used, the blade surface temperature can be reduced by up to 400°C to 500°C. The thermal insulation effect is 50℃~100℃, so the materia...

Claims

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Application Information

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IPC IPC(8): C22C30/00C22C1/02
CPCC22C30/00C22C1/02
Inventor 王梦宋佳星寇钢田权伟
Owner 西安稀有金属材料研究院有限公司