Powder metallurgy materials are special and have great potential in the aviation field!

    At present, the weight of commercial aircraft engines generally ranges from 2000kg to 8500kg, of which powder metallurgy materials account for 85% to 95% of the engine weight. Due to the unique combination of metal properties, including high strength and high toughness, it exhibits high degradation resistance and good surface in severe oxidizing and corrosive environments encountered during thermal engine cycles and during engine operation. Stability keeps it dominant.

     Powder metallurgy materials are special, and they play a huge role in aircraft engines!

     The temperature and pressure of the gas are determined by the thermodynamic cycle, so suitable materials must be found for every part of the engine-from the front-end fan to the compressor, combustor and turbine.

     For fans, low-density materials with high toughness are preferred as the blades. Titanium alloy and polymer matrix composite materials and some aluminum composite materials are popular and have greater productivity. After the airflow passes through the compressor, the temperature rises to 700°C. This part includes titanium alloy blades and discs.

    In the burner part, high-temperature nickel-based and cobalt-based alloys (with medium strength and easy processing) have become the main materials of the structure. After combustion, the gas temperature is in the range of 1400°C to 1500°C. As they enter the high-pressure turbine, the rotating turbine blades are subjected to the most severe stress and temperature combined test in the engine.

    Among them, the turbine blade is the most special aerodynamic thermal component, and its thin-walled and multi-layer structure drives a complex internal cooling system. At present, turbine blades are mainly made by applying an anti-oxidation intermetallic bonding coating on a single-crystal nickel-based super high-temperature alloy substrate, and then using porous, low-conductivity yttria-stabilized zirconia topcoat as Made of thermal barrier.

    The blades are attached to a turbine disc, which is made of a polycrystalline form of nickel-based alloy. As one of the safest and key parts of the engine, the disc is often formed by powder metallurgy and superplastic forging to maximize the strength and fatigue resistance.

    With the hot gas extraction from the turbine, the gas temperature drops again to a moderate level below 800°C. The rotating and stationary parts of the rear section of the turbine are mainly polycrystalline nickel-based superalloys. For the engine shaft, it must have high strength and fatigue resistance, usually composed of high-strength steel or nickel-based superalloy.