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

A nickel-based high-temperature alloy and aero-engine technology, applied in the field of composite materials, can solve problems such as easy oxidation, low heat-resistant temperature, and high heat-resistant temperature

Inactive Publication Date: 2014-03-05
魏玲
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  • Abstract
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  • Claims
  • Application Information

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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

Method used

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

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Embodiment 1

[0015] The material grade of the titanium alloy is Ti-6Al-4V, the thickness is 2mm, and its chemical composition is: aluminum: 5.5%-6.75%, vanadium: 3.5%-4.5%, and the balance is titanium. The material grade of nickel-based alloy is K4169, the thickness is 8mm, the chemical composition of K4169: aluminum: 0.5%, zirconium: 0.05%, titanium: 1.0%, manganese: 3.0%, niobium: 5.2%, chromium: 18.5%, nickel 52% , molybdenum: 3.0%, carbon: 0.05%, and the balance is iron. The charge height of the explosive is 30mm, and the gap is 5mm.

[0016] Among them, the titanium alloy Ti-6Al-4V has a series of advantages such as excellent corrosion resistance, small density, high specific strength, good toughness and weldability. The main alloying element of nickel-based alloy K4169 is nickel, which has high strength, fatigue life, fracture toughness and fatigue crack growth resistance.

[0017] Specific steps:

[0018] (1) A nickel-based superalloy / titanium alloy composite material for aeroeng...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B15/01B23P15/00
Inventor 段绵俊魏玲王录雁陈俊
Owner 魏玲
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