Copper alloy material and preparation method and application thereof

Abstract

The invention provides a copper alloy material and a preparation method and application thereof, and belongs to the technical field of additive manufacturing. The copper alloy material is prepared from the following components in percentage by mass: 2.0%-7.0% of Cr, 1.0%-5.0% of Nb, 0.1%-2.0% of Ag, 0.1%-0.7% of Zr, 0.02%-0.3% of RE and the balance of Cu; and the RE is prepared from the followingcomponents in percentage by mass: 88%-93% of La, 6%-9% of Ce, 1.5%-1.9% of Pr and less than or equal to 0.3% of Nd, and the sum of the mass percent is 100%. According to the copper alloy material, through the synergistic effect of RE, Cr, Nb, Ag, Zr and Cu, the heat-conducting property, high-temperature creep property, high-temperature strength and high-temperature fatigue of the copper alloy material are effectively improved, and the problem that in the prior art, the high-temperature mechanical property of the copper alloy material is poor is solved.

Description

technical field [0001] The invention belongs to the technical field of additive manufacturing, and in particular relates to a copper alloy material and a preparation method and application thereof. Background technique [0002] Modern aerospace grade components require high thermal conductivity, high temperature creep resistance, high temperature strength, high temperature fatigue and high mechanical properties. At present, there are few high-temperature-resistant copper alloy grades that meet the requirements of aerospace-grade components, such as: CuZr copper alloy, its chemical composition is Cu-Zr0.15-0.3%, and the chemical composition of CuAgZr copper alloy is Cu-Ag3.0%- Zr0.5%. These high-temperature-resistant copper alloy materials are binary alloys or ternary alloys, which are mostly produced by traditional centrifugal casting or forging spinning methods, and are mainly used in thrust chamber combustion chamber linings. [0003] However, in the actual thermal tests...

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Problems solved by technology

[0003] However, in the actual thermal tests of the hydrogen-oxygen rocket engine, it is often found that comb-like cracks appear on the inner wall of the thrust chamber of the hydrogen-oxygen rocket engine after multiple thermal tests, and the cracks expand slightly in the subsequent thermal tests, and the inner wall of the channel bulges into the combustion chamber. Since then, high-temperature creep occurs on the inner wall, and the cooling channel suffers from coil-shaped degradation and failure, which eventually leads to fracture and damage to the inner wall of the combustion chamber.

It can be seen that the high-temperature mechanical properties of existing copper alloy materials are poor and need to be further improved

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