Preparation method for high-temperature-resistant laminated composite zirconium dioxide-niobium material

Abstract

The invention relates to a preparation method for a high-temperature-resistant laminated composite zirconium dioxide-niobium material. The preparation method comprises the following steps: preprocessing of a niobium sheet, zirconium plasma injection, drawing of a zirconium dioxide film on the surface of the niobium sheet through the sol-gel method, and high-temperature sintering. The invention has the advantages that through the vacuum metal plasma injection technology, the metallic element zirconium is injected into the pickled and etched niobium metal test sheet according to a certain amount of energy and dosage, so as to solve the problem that the zirconium dioxide film easily cracks due to the large differences between niobium and zirconium dioxide in ion size as well as between coefficients of thermal expansion; the niobium metal test sheet is covered by the zirconium dioxide film through the vertical drawing method of a zirconium sol-gel solution; the niobium sheet and the zirconium dioxide film are subjected to high-temperature annealing and sintering together to prepare the high-temperature-resistant laminated composite zirconium dioxide-niobium material. According to the composite zirconium dioxide-niobium material, the niobium sheet and the zirconium dioxide film are directly compounded in a laminated manner, so that the high-temperature-resistant property of the niobium sheet and the zirconium dioxide film is preserved. Therefore, the composite zirconium dioxide-niobium material achieves a very good application potential in the high-temperature field.

Description

technical field [0001] The invention belongs to the technical field of ceramic-metal layered composite material preparation and relates to a preparation process of zirconium dioxide-niobium high temperature resistant layered composite material. Background technique [0002] With the development of the aerospace industry, the requirements for high-temperature parts of aerospace vehicles are becoming more and more stringent. These requirements mainly include: high strength, high stiffness, good high temperature resistance, low temperature toughness and light weight. Existing high-temperature-resistant materials are generally nickel (Ni)-based materials, but Ni-based materials can withstand a maximum temperature of less than 1500°C. If the working temperature is higher, it cannot meet the needs, and new materials must be researched and developed to meet the requirements. [0003] Niobium (Nb) metal itself has the characteristics of high melting point (2467°C), low density, good...

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Problems solved by technology

Among them, the disadvantage of chemical vapor deposition is that the reaction temperature is high, corrosive gases (such as halogen compounds) exist in the reaction process, and the deposition rate is relatively low; PVD is an improved form of CVD, and this method has complex film-making equipment and cost High, the oxygen generated by the reaction is highly corrosive; the disadvantage of the electrophoretic deposition method is that the electrochemical reaction (such as water electrolysis, electroplating reaction, water electroosmosis, etc.) caused by the current passing through the electrode reduces the deposition efficiency and the sediment is uneven. ; The sputtering method prepares thin films under high vacuum, and the cost is high; the electron beam evaporation coating method is not suitable for refractory metals and high temperature resistant dielectric materials; when the tape casting method is used to manufacture large-area thin films, the slurry contains a large number of additives , it is easy to warp and crack during the sintering process; finally, the film prepared by plasma spray method is not dense and has more cracks

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