Multi-component ultrahigh-entropy lightweight refractory composite material

Abstract

The invention provides a multi-component ultrahigh-entropy light-weight refractory composite material. Four light alloy elements including Mo, Ti, Al and Nb are used as a matrix, non-metallic elements including Si, C, N, B and O are introduced into the matrix, and the composite material contains multiphase ceramics including TiC, TiB2, SiC, Si3N4, BC, MoSi2, Nb2O5, SiO2 and the like, so that the high-temperature strength and oxidation resistance of the matrix are effectively improved, and the low-density, high-temperature, high-toughness and long-term oxidation resistance performance of alloy can be achieved. According to the multi-component ultrahigh-entropy light-weight refractory composite material, the composite material is prepared through powder mixing, forming, sintering and pre-oxidation, and the anti-oxidation time of the composite material in the air environment of 800-1500 DEG C is 100-300 h; the room-temperature tensile strength is 600-1000 MPa, and the ductility is greater than or equal to 10%; and the density is 4.5-5.5 g / cm<3>. The multi-component ultrahigh-entropy light-weight refractory composite material is suitable for the fields of aviation, spaceflight, weapons, nuclear energy, microelectronics and the like.

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