Rich chromium evolution phase reinforcing high chromated nickel base high-temperature alloy and preparation thereof

Abstract

The invention discloses a high-Chromium-Nickel based high-temperature alloy strengthened by Chromium-rich precipitated phase and a preparation method, and belongs to the field of high-temperature alloy steel, in particular to high-temperature alloy parts with high-strength and anticorrosion used below 1350 DEG C. The high-Chromium-Nickel based high-temperature alloy of the invention has the following components which are in weight percent: 35 to 40 percent of Chromium, smaller than 0.01 of Carbon, 0.01 to 3 percent of Aluminum, 0.01 to 3 percent of Titanium, and the remaining components are Nickel and other inevitable impurity elements. The preparation method thereof is carried out as follows: the compound of the raw material comprising the elements is melted, moulded, forged or rolled successively, firstly solution treatment of 1100 to 1200 DEG C in 30 minutes to 1 hour is carried out, then the compound is treated in two-stage aging treatment. After the heat treatment, the granular precipitated phase of Chromium-rich Alpha-Chromium in high density is evenly distributed in austenite matrix, the size is between 0.1 to 2 Mu meter, thus the optimal matching of organization is realized and plasticity and toughness as well as strength of alloy is assured. Compared with the prior art, the high-Chromium-Nickel based high-temperature alloy has not only the excellent performance of antioxidation and hot corrosion resistance, but also the stable microstructure and the excellent mechanical property by using Alpha-Chromium as a strengthening phase, in particular has the comprehensive performance in high-temperature and hot corrosion environment which is obviously better than that of the existing alloy.

Description

technical field [0001] The invention belongs to the field of alloy steel for high temperature. It is especially suitable for high-strength heat-resistant and corrosion-resistant superalloy parts used below 1350°C. Background technique [0002] Combustion chambers are critical heat-bearing components in aerospace engines. The processes of fuel atomization, oil-gas mixing, ignition and combustion are all carried out in the combustion chamber (the part except the shell is also called the flame tube). Therefore, the combustion chamber is the area with the highest temperature among all parts of the engine. When the temperature of the gas in the combustion chamber is as high as 1500°C to 2000°C, the temperature of the chamber wall alloy can reach above 800°C to 900°C, and locally it can reach 1100°C. Therefore, the mechanical stress suffered by the combustion chamber is small, but the thermal stress is relatively large. The requirements for materials mainly include: high tempera...

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Problems solved by technology

Therefore, for the comprehensive performance requirements of combustion chamber materials, conventional high-temperature alloys cannot further increase the Cr content, and cannot break through the requirements of oxidation resistance and gas corrosion resistance, and cannot increase the gas temperature, thereby failing to further improve the engine's ability.

At present, there are also surface treatment methods such as coatings to improve the high-temperature oxidation resistance and hot corrosion resistance of alloys. Although they can meet the requirements, they are often limited by size and shape and there are certain hidden dangers [Xun Baiqiu, Li Qi, Zhao Wuen. High-temperature materials in Application and Development of Gas Turbines, Thermal Power Engineering, 2004, 19(5): 447]

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