| GH3030 | |||||||||||||||||||
| Gh3030 | |||||||||||||||||||
| brief introduction | 80Ni-20Cr solid solution-strengthened superalloy features a simple chemical composition. It exhibits satisfactory thermal strength and high plasticity at temperatures below 800°C, along with excellent resistance to oxidation and thermal fatigue, as well as superior cold stamping and welding performance. Following solution treatment, the alloy consists of single-phase austenite, maintaining a stable microstructure during service. | ||||||||||||||||||
| Chemical Composition Wt.% | % | Fe | Cr | P | Cu | Ni | Al | Ti | C | Mn | Si | V | S | ||||||
| Min | 19 | Balance | 0.15 | ||||||||||||||||
| Max | 1.5 | 22 | 0.03 | 0.20 | Balance | 0.15 | 0.35 | 0.12 | 0.7 | 0.8 | 0.50 | 0.02 | |||||||
| Physical Constants | Density | 8.4g/cm³ | |||||||||||||||||
| Melting Range | 1374-1420℃ | ||||||||||||||||||
| Mechanical Constants | Alloy state | Tensile Strength(MPA) Rm N/mm2 | Yield Strength(MPA) RP0.2N/mm2 | Elongation A5% | |||||||||||||||
| Solution Treated | 785 | 270 | 35 | ||||||||||||||||
| Applications | It is primarily used for turbine engine combustor components operating below 800°C, as well as other high-temperature parts requiring oxidation resistance under minimal loads at temperatures up to 1100°C. | ||||||||||||||||||
| GH3039 | |||||||||||||||
| GH3039 | |||||||||||||||
| brief introduction | GH3039 is a single-phase austenitic solid solution-strengthened alloy. It exhibits moderate thermal strength and good thermal fatigue properties at temperatures below 800°C, with excellent oxidation resistance up to 1000°C. The microstructure remains stable during long-term service, and the alloy also offers superior cold formability and weldability. It is suitable for aero-engine combustor and afterburner components designed for long-term operation at temperatures up to 850°C. The alloy is available in the form of sheets, bars, wires, tubes, and forgings. | ||||||||||||||
Chemical Composition Wt.% | % | Ni | Cr | Mo | Nb | Fe | Ti | C | Mn | Si | Al | P | S | B | |
| Min | Balance | 19 | 1.8 | 0.9 | 0.35 | 0.35 | |||||||||
| Max | Balance | 22 | 2.3 | 1.3 | 3.0 | 0.75 | 0.08 | 0.4 | 0.80 | 0.75 | 0.02 | 0.012 | |||
| Physical Constants | Density | 8.3g/cm³ | |||||||||||||
| Melting Point | 900-1170℃ | ||||||||||||||
| Applications | Applications: Aero-engine combustor flame tubes, afterburner casings, and nozzle segments (adjustment flaps). Structural components for gas turbine combustion chambers. Combustor parts and components for turbine engines. Afterburner components. | ||||||||||||||
| GH3044 | ||||||||||||||||
| GH3044 | ||||||||||||||||
| brief introduction | GH3044 is a solid solution-strengthened nickel-based oxidation-resistant alloy. It exhibits high plasticity and moderate thermal strength at temperatures below 900°C, along with excellent oxidation resistance and superior stamping and welding performance. It is well-suited for the manufacturing of main combustor and afterburner components, as well as heat shields and guide vanes, designed for long-term service in aero-engines operating below 900°C. | |||||||||||||||
| Chemical Composition Wt.% | % | Ni | Cr | Fe | Mo | Mn | Al | Ti | W | C | Si | P | S | Cu | ||
| Min | Balance | 23.5 | 0.3 | 13.0 | ||||||||||||
| Max | Balance | 26.5 | 4.0 | 1.5 | 0.5 | 0.5 | 0.7 | 16.0 | 0.1 | 0.8 | 0.013 | 0.013 | 0.07 | |||
| Physical Constants | Density | 8.89g/cm³ | ||||||||||||||
| Melting Point | 1352-1375℃ | |||||||||||||||
| Applications | Applications: Aero-engine combustor flame tubes, afterburner casings, and nozzle segments (adjustment flaps). Structural components for gas turbine combustion chambers. Combustor parts and components for turbine engines. Afterburner components. | |||||||||||||||
| GH3128 | ||||||||||||||||
| GH3128 | ||||||||||||||||
| brief introduction | GH3128 is a solid solution-strengthened nickel-based superalloy with no direct equivalent American grade (ASTM). It offers excellent comprehensive performance and a long stress-rupture life, characterized by high plasticity, high creep-rupture strength, good oxidation resistance, and superior stamping and welding properties. Its overall performance is superior to that of similar nickel-based solid-solution alloys, such as GH3044 and GH3536. | |||||||||||||||
| Chemical Composition Wt.% | % | Ni | Cr | Mo | W | Fe | Ti | C | Mn | Si | Al | P | S | B | ||
| Min | Balance | 19 | 7.5 | 7.5 | 0.4 | 0.4 | ||||||||||
| Max | Balance | 22 | 9.0 | 9.0 | 2.0 | 0.8 | 0.05 | 0.5 | 0.80 | 0.8 | 0.013 | 0.013 | 0.01 | |||
| Physical Constants | Density | 8.81g/cm³ | ||||||||||||||
| Melting Point | 1364-1424℃ | |||||||||||||||
| Applications | Applications: Aero-engine combustor flame tubes, afterburner casings, and nozzle segments (seal tabs). Structural components for gas turbine combustion chambers. Combustion chamber parts and components for turbine engines. Afterburner components. | |||||||||||||||
| GH4080A | |||||||||||||||||
| GH4080A | |||||||||||||||||
| brief introduction | GH4080A is a nickel-based superalloy composed of Ni-Cr. It exhibits excellent high-temperature strength along with outstanding corrosion and oxidation resistance. These advantages lead to the wide application of GH4080A in high-temperature hot-forged components across industries such as aviation, aerospace, power generation, and transportation. | ||||||||||||||||
| Chemical Composition Wt.% | % | Ni | Cr | Fe | Mo | Mn | Al | Ti | W | C | Si | P | S | Cu | |||
| Min | Balance | 18.0 | 1.0 | 0.3 | |||||||||||||
| Max | Balance | 21.0 | 1.8 | 0.7 | 0.1 | 1.0 | 0.015 | ||||||||||
| Physical Constants | Density | 8.19g/cm³ | |||||||||||||||
| Melting Point | 1320-1365℃ | ||||||||||||||||
| Applications | Applications: Aero-engine combustor flame tubes, afterburner casings, and nozzle segments (adjustment flaps). Structural components for gas turbine combustion chambers. Combustor parts and components for turbine engines. Afterburner components. | ||||||||||||||||
