FIELD: metallurgy.
SUBSTANCE: invention relates to metallurgy, namely to metal-matrix composite based on heat-resistant titanium alloy, and can be used in aircraft engineering when making parts of aircraft engines. Metal matrix composite Ti-6.5Al-2Zr-1Mo-1V/TiB2 contains a matrix of heat-resistant titanium alloy, at.%: titanium 89.5, aluminium 6.5, zirconium 2.0, molybdenum 1.0, vanadium 1.0, and reinforcing component TiB2 in amount of 2–3 wt.%, wherein the composite is obtained by vacuum-arc remelting of titanium, aluminium, zirconium, molybdenum, vanadium with addition of TiB2 powder with average particle size of 4 mcm.
EFFECT: material is characterized by high strength and plasticity at room and high temperatures.
1 cl, 2 dwg, 2 tbl, 2 ex
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