The aviation industry has extremely strict requirements for materials: stability at high temperatures, high creep strength, good fatigue properties, slow crack propagation, toughness, and resistance to high-temperature oxidation.
When an aircraft is flying at high altitudes, the pressurized cabin of the fuselage is subjected to internal pressure. Therefore, materials with high tensile strength and good fatigue resistance, such as hard aluminum, are required for the skin. The fuselage frames usually use ultra-hard aluminum, while the strengthened frames that bear larger loads are made of high-strength structural steel or titanium alloys.
The wing is the main component of an aircraft. The early low-speed aircraft had wooden wings with fabric as the skin. This type of wing had low structural strength and poor aerodynamic efficiency and has long been replaced by metal wings. The beams inside the wing are the main load-bearing components of the wing, usually made of ultra-hard aluminum, steel or titanium alloy; the joint parts between the wing beams and the fuselage are made of high-strength structural steel.
When designing the turbine casing of an aircraft engine, it is necessary to ensure high stability because it must withstand the tremendous impact force caused by the fragmentation of the blades in case of technical damage. Therefore, the turbine casing is generally made of titanium alloys, Inconel chromium-nickel-iron alloys, or Waspalloy nickel-based superalloys. Additionally, the turbine discs, which belong to the components of an aircraft engine, are reinforced with aramid fibers and are made of titanium 64, high-temperature alloy Inconel 718, or Udimet 720.
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