A multi-component ultra-high entropy lightweight refractory composite material

Abstract

The invention provides a multi-component ultra-high entropy lightweight refractory composite material. The material uses four light alloy elements Mo, Ti, Al, and Nb as a matrix, and introduces Si, C, N, and B into the matrix. , O non-metallic elements, so that the composite material has TiC, TiB 2 , SiC, Si 3 N 4 , BC, MoSi 2 , Nb 2 o 5 , SiO 2 Multi-phase ceramics such as multi-phase ceramics effectively improve the high temperature strength and oxidation resistance of the matrix, thereby realizing its low density, high temperature high toughness and long-term oxidation resistance. The present invention prepares composite materials through powder mixing, molding, sintering, and pre-oxidation. The anti-oxidation time of the material is 100-300h in the air environment of 800-1500°C; the tensile strength at room temperature is 600-1000MPa, and the elongation is ≥10%; the density is 4.5-5.5g / cm 3 . It is suitable for aviation, aerospace, weapons, nuclear energy, microelectronics and other fields.

Description

technical field [0001] The invention relates to the field of high-temperature thermal protection materials, in particular to a multi-component ultra-high-entropy lightweight refractory composite material. Background technique [0002] With the development of cutting-edge technology, the hot-end components of aircraft and aero-engines put forward extremely high requirements for high-temperature materials. For example, if the aircraft is used for long-term cruise flight and repeated use at low altitudes at Ma0-6, it is required that the large-area skin is resistant to high temperatures of 800-1200°C, lightweight, anti-oxidation, and anti-ablation. Another example is that the temperature in front of the turbine of a new generation of aero-engine is as high as 2100K, and the turbine blades are required to withstand high temperatures above 1500°C under the cooling effect of the cooling gas, and at the same time withstand high-pressure gas erosion. Existing high-temperature mater...

AI Technical Summary

Problems solved by technology

Existing high-temperature materials commonly used in aerospace, such as titanium alloys, superalloys, intermetallic compounds, ceramic matrix composites, and refractory metals, cannot meet the requirements: titanium alloys have a low density, but can only be used below 600°C; superalloys It can be used at 900-1100°C, and can be used at 1100-1300°C for a long time after surface coating, but the high-temperature alloy has a high density on the one hand, and the surface thermal barrier coating will crack and peel off when it is used for a long time. Its work is unstable; the low density of TiAl intermetallic compounds can have good high-temperature strength and toughness at 800-900 ° C, but its room temperature brittleness is large, and it cannot be processed and deformed into thin plates and sheets. At the same time, when the temperature is higher than 1000 ° C When the material strength and toughness drop sharply; the ceramic matrix composite material has low density and good oxidation resistance, but its high temperature performance and thermal loadability are poor, and there is a greater risk of unreliability when it can be reused for a long time; Molten metal can be used above 1600°C, but it needs to be coated and has a high density, which limits its use