Features and applications
Inconel 718 (UNSN07718/ W.Nr. 2.4668) is a nickel-chromium alloy material with high strength and good corrosion resistance. It is generally used in the temperature range of -423° to 1300°F. This aging alloy can be easily manufactured and can be manufactured into a variety of complex parts. Alloy 718 has good welding characteristics and has a particularly strong resistance to cracking after welding. Inconel 718 has excellent tensile, creep, fatigue, and fracture strengths, and good workability, so it is widely used in industry. For example, liquid fuel rocket components, rings, shells, and variously shaped sheet metal parts for aircraft and land-based gas turbine engines, and cryogenic tanks. In addition, it is also used for fasteners and instrument parts.
Inconel X-750(UNSN07750/W.Nr. 2.4669) is a precipitation-hardenable nickel-chromium alloy with good corrosion and oxidation resistance. It still has good mechanical properties and strength at a temperature of 1300°F. When the temperature exceeds 1300°F, the effect of precipitation hardening will disappear, but the effective strength of the heat-treated material can reach 1800°F. Alloy X-750 alloy also has excellent low-temperature performance. Inconel X-750 is often used in large pressure vessels and is also widely used in the manufacture of gas turbines, such as rotor blades, wheels, bolts, and other structural components. It is also used in rocket engine thrust chambers, and airframe applications include thrust reversers and hot air duct systems.
Heat treatment method
Inconel 718--For most applications, Inconel Alloy 718 is specified as solution annealing and precipitation hardening. Alloy 718 is hardened by secondary phase precipitation into a metal matrix. The precipitation of these nickel (aluminum, titanium, niobium) phases is induced by heat treatment in the temperature range of 1100 to 1500°F. In order for a metallurgical reaction to occur, the aging components (aluminum, titanium, niobium) must be in solution; if they are precipitated as other phases or combined in other forms, they cannot be properly precipitated and the full strength of the alloy cannot be obtained. To perform this function, the material must first undergo a solution heat treatment.
Inconel 718 alloy usually uses two heat treatments:
• Solution annealing at 1700-1850°F, then rapid cooling (usually in water), then precipitation hardening at 1325°F for 8 hours, furnace cooling to 1150°F and holding at 1150°F for 18 hours The total aging time is then air-cooled.
• Solution annealing at 1900-1950°F, then rapid cooling (usually in water), then precipitation hardening at 1400°F for 10 hours, furnace cooling to 1200°F, and a total of 20 hours at 1200°F Aging time, then air cooling.
If the material is to be machined, formed, or welded, it is usually annealed or stress-relieved in the rolling mill situation. The material is then manufactured under its most ductile conditions.
Inconel X-750--Depending on the application and required performance, Inconel X-750 will use different heat treatment methods. For use above 1100°F, especially when it needs to bear the load for a long time, through solution treatment (2100°F) + stabilization treatment (1550°F) + precipitation treatment (1300°F), Obtain the best mechanical properties. When the temperature is lower than 1100°F, the alloy can be strengthened by precipitation treatment after hot or cold working or precipitation treatment after homogenization or solution treatment. Furnace cold treatment is also used to develop an optimal performance for certain applications.
Chemical composition comparison
|Grade||C||Cr||Nb(Plus Ta)||Mo||Co||Mn||Ti||P||Fe||Ni(Plus Co)||B||Al||Si||S||Cu|
Comparison of physical and mechanical properties
|Physical and mechanical properties|
|Grade||Density||Melting Point||Tensile Strength||Yield Strength (0.2% Offset)||Elongation|
|Inconel 718||8.17 g/cm3||2300-2437°F||550 MPa||220 MPa||30%|
|Inconel X-750||8.28 g/cm3||2540-2600°F||1267 MPa||868 MPa||25%|
Supplier of Inconel 718 & Inconel X-750
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