A composite material includes: coated particles, each of which includes a carbon-based particle made of a carbon-based substance and a carbide layer that covers at least a part of the surface of the carbon-based particle; and a copper phase that binds the coated particles to each other, wherein the carbide layer is made of a carbide containing at least one element selected from the group consisting of Si, Ti, Zr and Hf, and the average particle size of the carbon-based particles is 1 m or more and 100 m or less.

An aluminum composite material (1, 2, 3, 4, 5) is a composite formed of an aluminum fiber structure (10) and a composite material (70, 80, 110). The aluminum fiber structure (10) includes aluminum fibers (20) partially bound to each other, and alumina layers 30 are formed on surfaces of the aluminum fibers (20). A plurality of alumina protrusions (40) each having a height larger than a thickness of the alumina layer (30) are formed on surfaces of the aluminum fibers (20) or the alumina layers (30). The alumina protrusions (40) and at least a part of the composite material (70, 80, 110) are in contact with each other.

A method of forming a metal matrix composite component includes positioning a preform including an electrically non-conductive fibrous material in a shaping tool. The fibrous material is pre-coated. The method includes flowing a molten metal comprising zinc into the shaping tool so that at least a portion of the preform is enveloped by the molten metal to form the metal matrix composite component; and cooling the metal matrix composite component.

This disclosure, and the exemplary embodiments provided herein, disclose carbon nanotubes (CNT) integrated into 316L stainless steel (SS) powder feedstocks and 3D-printed using selective laser melting (SLM). Ball milling is used to disperse CNT clusters homogeneously onto the surface of 316L SS powders with minimal damage to the CNTs. Hardness increased by 35% and wear was reduced by 70% with the addition of 2 vol % CNT, relative to SLM 316L SS. The addition of CNTs increased the water contact angle and retained the desirable corrosion resistance of SLM 316L SS, demonstrating the potential of 3D-printed SS-CNT composites for use in structural marine applications.

This disclosure, and the exemplary embodiments provided herein, disclose carbon nanotubes (CNT) integrated into 316L stainless steel (SS) powder feedstocks and 3D-printed using selective laser melting (SLM). Ball milling is used to disperse CNT clusters homogeneously onto the surface of 316L SS powders with minimal damage to the CNTs. Hardness increased by 35% and wear was reduced by 70% with the addition of 2 vol % CNT, relative to SLM 316L SS. The addition of CNTs increased the water contact angle and retained the desirable corrosion resistance of SLM 316L SS, demonstrating the potential of 3D-printed SS-CNT composites for use in structural marine applications.

The present disclosure discloses a continuous electrophoretic deposition modified carbon fiber reinforced multi-matrix composite and a preparation method thereof, composing of a carbon fiber with a volume fraction of 30-55%, an inorganic powder with a volume fraction of 3-25% and a matrix with a volume fraction of 20-67%, wherein the inorganic powder is wrapped on the surface of the carbon fiber filament or embedded in the carbon fiber bundle, and the concentration gradually decreases from the fiber filament to the surface of the fiber bundle. The preparation method of the composite is as follows: (1) pretreating the carbon fibers; (2) preparing a slurry of the inorganic powder; (3) widening the pretreated carbon fiber to form a carbon fiber strip, and then carrying out electrophoretic deposition on the inorganic powders; (4) preparing a preform from the deposited carbon fibers; and (5) compounding a matrix in the preform.

A gas turbine engine component includes a component including at least one ceramic matrix composite material, the at least one ceramic matrix composite material further includes a ceramic fiber reinforcement containing at least one ceramic fiber or at least one ceramic fiber tow; and a matrix material disposed around and in contact with the at least one ceramic fiber or the at least one ceramic fiber tow; the matrix material contains at least one eutectic alloy, at least one metal-rich alloy, or combinations thereof; either the at least one eutectic alloy or the at least one metal-rich alloy includes silicon and at least one of the following alloy constituents: zirconium, hafnium, tungsten, tantalum, molybdenum, niobium, and iridium; and, either the at least one eutectic alloy or the at least one metal-rich alloy exhibits and possesses a melting point range of approximately 1,250 C. to approximately 1,650 C.

A gas turbine engine component includes a component including at least one ceramic matrix composite material, the at least one ceramic matrix composite material further includes a ceramic fiber reinforcement containing at least one ceramic fiber or at least one ceramic fiber tow; and a matrix material disposed around and in contact with the at least one ceramic fiber or the at least one ceramic fiber tow; the matrix material contains at least one eutectic alloy, at least one metal-rich alloy, or combinations thereof; either the at least one eutectic alloy or the at least one metal-rich alloy includes silicon and at least one of the following alloy constituents: zirconium, hafnium, tungsten, tantalum, molybdenum, niobium, and iridium; and, either the at least one eutectic alloy or the at least one metal-rich alloy exhibits and possesses a melting point range of approximately 1,250 C. to approximately 1,650 C.