Nickel-base high-temperature alloy/titanium alloy composite material for aero-engine

Abstract

The present invention discloses a nickel-base high-temperature alloy / titanium alloy composite material for aero-engine. The material comprises the following three layers of metal materials: a nickel-base high-temperature alloy plate (2) on the upper layer, a nickel-base high-temperature alloy plate (5) on the lower layer and a titanium alloy plate (4) in the middle layer, wherein the material trademark of the titanium alloy is Ti-6Al-4V, the chemical components of the titanium alloy comprise 5.5-6.75% of aluminum, 3.5-4.5% of vanadium, and the balance of titanium, the material trademark of the nickel-base alloy is K4169, and the chemical components of the nickel-base alloy comprise 0.5% of aluminum, 0.05% of zirconium, 1.0% of titanium, 3.0% of manganese, 5.2% of niobium, 18.5% of chromium, 52% of nickel, 3.0% of molybdenum, 0.05% of carbon, and the balance of iron. According to the present invention, the bonding rate of the composite material achieves 100% and achieves metallurgical bonding, the nickel-base high-temperature alloy has characteristics of high temperature ablation resistance and high high-temperature strength, and can be used for a long time at a high temperature, the titanium alloy can provide a structure support effect, and the composite material has characteristics of light weight, high temperature resistance and high strength, and is a novel aircraft engine composite material with characteristics of light weight, high strength and high temperature resistance.

Description

technical field [0001] The invention relates to a nickel-based high-temperature alloy / titanium alloy composite material used for an aeroengine, and belongs to the field of composite materials. Background technique [0002] Titanium alloy has low density and high specific strength. Compared with nickel-based superalloy, its density is much lower, so it is a very promising light-weight and high-temperature resistant structural material. However, the heat resistance temperature of titanium alloy is lower than that of nickel-based superalloy, and it is easy to be oxidized above 850°C. Therefore, producing a composite material with titanium alloy inside and nickel-based superalloy outside can combine the advantages of the two materials. The blade made of this material has the advantages of light overall weight but high heat resistance temperature. Contents of the invention [0003] Purpose of the invention: In view of the deficiencies in the prior art, the purpose of the inven...

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Problems solved by technology

However, the heat resistance temperature of titanium alloy is lower than that of nickel-based superalloy, and it is easy to be oxidized above 850°C. Therefore, producing a composite material with titanium alloy inside and nickel-based superalloy outside can combine the advantages of the two materials. The blade made of this material has the advantages of light overall weight but high heat resistance

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