At the beginning of the 21st century, the economy and aviation market suffered severe crises, leading to the development of more efficient products by aircraft and engine manufacturers. The new generation of aircraft has improved aerodynamics, increased the use of composite materials and new aluminum alloys, and new manufacturing processes that help reduce weight. Aeroengines provide some of the most demanding applications for structural materials. Modern turbine engines operate at high temperatures and pressures, and engine components are often affected by destructive corrosion, oxidation and erosion conditions. These engines convert fuel energy into propulsion thrust. In the past few decades, higher engine performance has been achieved by increasing the turbine gas temperature and increasing the efficiency of each engine stage. Since the development of gas turbine engines for defense jet aircraft, the application of materials at high temperatures has been studied. The term superalloy was first used to describe superalloys in the mid-1940s. Not only can it be used at high temperatures, but it can also maintain its strength and toughness at high temperatures. The term refers to nickel alloys and cobalt alloys.
Super alloys are mainly used in the manufacture of gas turbine components, such as blades, rotors and vanes. These applications are the result of early development, initially used in military and civil aviation, and later transferred to the power generation industry. Two technologies are closely related to the production and development of superalloy parts: vacuum furnace technology and investment casting. In addition, the complex geometries of gas turbine components (such as blades and rotors) do not allow extensive use of machining processes. In this sense, the use of investment casting technology is decisive for the success of Inconel 713C superalloy products.
For most applications, Inconel alloys are specified as: solution annealing and precipitation hardening (age hardening). Inconel 713C is hardened by the precipitation of the second phase (for example, γ'and carbide) into the metal matrix. The precipitation of these nickel (aluminum, titanium and niobium) phases is caused by heat treatment in the temperature range of 600 to 950 °C. In order for this metallurgical reaction to occur correctly, the stable components (aluminum, titanium, niobium) must be in solution (dissolved in the matrix); if they precipitate in the form of other phases or combine in other forms, they will not precipitate properly and The full strength of the alloy cannot be achieved. To perform this function, the material must first undergo a solution heat treatment (solution annealing is a synonym).
As a professional manufacturer of nickel-cobalt alloy materials, we already have proficient casting technology and material research for alloy 713C. We have been committed to solving the practical application of material value-added technology in complex environments, and have a solid foundation for material development and material solution capabilities.