Nickel Based Alloys - Plus Metals

NICKEL BASED ALLOYS

WASPALLOY

Waspalloy (UNS N07001) is a nickel-based superalloy characterized by its outstanding strength and oxidation resistance at high temperatures. This alloy is commonly used in aerospace components due to its high tensile strength and creep resistance. The specifications AMS 5708 and ASTM B637 highlight its suitability for applications requiring durability and performance under extreme conditions. Similarly, its designation under BS HR 201 and DIN 2.4654 further confirms its robust nature, making it an excellent choice for high-stress environments.

Composition
  • Carbon (C): Min 0.02%, Max 0.10%
  • Manganese (Mn): Max 1.00%
  • Silicon (Si): Max 0.75%
  • Phosphorus (P): Max 0.030%
  • Sulfur (S): Max 0.030%
  • Chromium (Cr): Min 18.0%, Max 21.0%
  • Cobalt (Co): Min 12.0%, Max 15.0%
  • Molybdenum (Mo): Min 3.5%, Max 5.0%
  • Iron (Fe): Max 2.0%
  • Aluminum (Al): Min 1.20%, Max 1.60%
  • Titanium (Ti): Min 2.75%, Max 3.25%
  • Boron (B): Min 0.003%, Max 0.010%
  • Zirconium (Zr): Min 0.02%, Max 0.12%
  • Copper (Cu): Max 0.50%
  • Nitrogen (N): 58 Bal
Properties
  • Density: Approximately 8.4 g/cm³.
  • Thermal Conductivity: ~12 W/m·K.
  • Tensile Strength: High tensile strength at elevated temperatures.
  • Oxidation Resistance: Excellent at high temperatures.
Applications
  • WASPALLOY is widely used in aerospace for its ability to withstand high temperatures and stresses, making it ideal for turbine blades and other critical engine parts.
Advantages
  • High-Temperature Strength: Maintains strength at elevated temperatures.
  • Oxidation Resistance: Good resistance to oxidation and corrosion.
Limitations
  • Cost: Expensive due to high nickel content.
  • Machinability: Difficult to machine.

INCONEL X750

Inconel X750 (UNS N07750) is another nickel-chromium-based superalloy, noted for its excellent oxidation resistance and mechanical properties at elevated temperatures. It is widely used in gas turbines and other high-temperature applications. Specified under AMS 5540 and ASTM B637, Inconel X750 is designed to withstand thermal cycling and harsh environments, ensuring reliability and extended service life.

Composition
  • Carbon (C): Max 0.08%
  • Manganese (Mn): Max 1.00%
  • Silicon (Si): Max 0.50%
  • Sulfur (S): Max 0.01%
  • Chromium (Cr): Min 14.0%, Max 17.0%
  • Aluminum (Al): Min 0.40%, Max 1.00%
  • Iron (Fe): Min 5.00%, Max 9.00%
  • Titanium (Ti): Min 2.25%, Max 2.70%
  • Copper (Cu): Max 0.50%
  • Nickel (Ni): Balance
Properties
  • Density: Approximately 8.3 g/cm³.
  • Thermal Conductivity: ~11 W/m·K.
  • Tensile Strength: Excellent tensile strength at high temperatures.
  • Oxidation Resistance: Excellent resistance to oxidation and carburization.
Applications
  • INCONEL X750 is commonly used in aerospace for its ability to endure extreme temperatures and stresses. It is ideal for turbine blades, vanes, and other critical engine parts.
Advantages
  • High Temperature Strength: Maintains mechanical properties at elevated temperatures.
  • Good Oxidation Resistance: Performs well in oxidizing and carburizing environments.
Limitations
  • Cost: High cost due to complex alloying and processing.
  • Machinability: Can be challenging to machine due to its hardness and strength.

INCONEL 945

Inconel 945 (UNS N09945), with its specifications W.NR.2.4652 and API 6ACRA, is tailored for highly corrosive and high-temperature applications, such as in the oil and gas industry. Its resistance to aggressive environments and high strength make it suitable for critical components exposed to extreme conditions.

Composition
  • Carbon (C): Min 0.005%, Max 0.04%
  • Manganese (Mn): Max 1.00%
  • Silicon (Si): Max 0.50%
  • Phosphorus (P): Max 0.03%
  • Sulfur (S): Max 0.03%
  • Nickel (Ni): Min 45.0%, Max 55.0%
  • Chromium (Cr): Min 19.5%, Max 23.0%
  • Molybdenum (Mo): Min 3.0%, Max 4.0%
  • Niobium (Nb): Min 2.5%, Max 4.5%
  • Copper (Cu): Min 1.5%, Max 3.0%
  • Titanium (Ti): Min 0.5%, Max 2.5%
  • Aluminum (Al): Min 0.01%, Max 0.7%
  • Iron (Fe): Balance
Properties
  • Density: Approximately 8.3 g/cm³.
  • Thermal Conductivity: ~11 W/m·K.
  • Tensile Strength: Excellent tensile strength at high temperatures.
  • Oxidation Resistance: Superior resistance to oxidation and corrosion.
Applications
  • INCONEL 945 is extensively used in the oil and gas industry for components that are exposed to high pressure and corrosive environments, such as wellhead equipment and pressure vessels.
Advantages
  • High Corrosion Resistance: Outstanding resistance to oxidation and corrosion.
  • High Temperature Strength: Maintains mechanical properties under extreme temperatures.
Limitations
  • Cost: High cost due to the alloy's complex composition.
  • Machinability: Can be difficult to machine and process.

INCONEL 945X

Inconel 945X (UNS N099456MS) offers enhanced properties over standard Inconel 945, providing even greater strength and stability. The alloy, covered under AMS 5780 and ASTM B637, is ideal for applications requiring superior resistance to oxidation and creep, extending its use in advanced aerospace and industrial settings.

Composition
  • Carbon (C): Min 0.005%, Max 0.04%
  • Manganese (Mn): Max 1.00%
  • Silicon (Si): Max 0.50%
  • Phosphorus (P): Max 0.03%
  • Sulfur (S): Max 0.03%
  • Nickel (Ni): Min 45.0%, Max 55.0%
  • Chromium (Cr): Min 19.5%, Max 23.0%
  • Molybdenum (Mo): Min 3.0%, Max 4.0%
  • Niobium (Nb): Min 2.5%, Max 4.5%
  • Copper (Cu): Min 1.5%, Max 3.0%
  • Titanium (Ti): Min 0.5%, Max 2.5%
  • Aluminum (Al): Min 0.01%, Max 0.7%
  • Iron (Fe): Balance
Properties
  • Density: About 8.6 g/cm³.
  • Thermal Conductivity: ~11 W/m·K.
  • Tensile Strength: Superior high-temperature strength.
  • Oxidation Resistance: Very good.
Applications
  • INCONEL 945X is used extensively in aerospace for turbine blades, engine components, and exhaust systems where high temperature and stress resistance is crucial.
Advantages
  • Enhanced Strength: Improved mechanical properties at high temperatures.
  • Corrosion Resistance: Excellent performance in harsh conditions.
Limitations
  • Cost: High due to advanced composition.
  • Machinability: Difficult machining process.

NIMONIC C263

Nimonic C263 (UNS N07263) is known for its high strength and good fatigue resistance at elevated temperatures. Specifications such as AMS 5888 and DIN 2.4660 reflect its suitability for high-stress applications where resistance to creep and thermal stability are essential, particularly in aerospace and power generation industries.

Composition
  • Carbon (C): Min 0.040%, Max 0.080%
  • Manganese (Mn): Max 0.60%
  • Silicon (Si): Max 0.40%
  • Aluminum (Al): Max 0.60%
  • Sulfur (S): Max 0.0070%
  • Nickel (Ni): Max 49.0%
  • Iron (Fe): Max 0.70%
  • Copper (Cu): Max 0.20%
  • Boron (B): Max 0.0050%
  • Cobalt (Co): Min 19.0%, Max 21.0%
  • Chromium (Cr): Min 19.0%, Max 21.0%
  • Molybdenum (Mo): Min 5.60%, Max 6.10%
  • Titanium (Ti): Min 1.90%, Max 2.40%
Properties
  • Density: Approximately 8.3 g/cm³.
  • Thermal Conductivity: ~14 W/m·K.
  • Tensile Strength: High tensile strength, particularly at elevated temperatures.
  • Oxidation Resistance: Excellent resistance to oxidation and carburization.
Applications
  • NIMONIC C263 is used extensively in aerospace applications for turbine blades, engine components, and exhaust systems where high temperature and stress.
Advantages
  • High Strength: Maintains exceptional strength at high temperatures.
  • Excellent Corrosion Resistance: Performs well in aggressive environments, including oxidation and carburization.
Limitations
  • Cost: High cost due to the complex alloying and processing.
  • Machinability: Difficult to machine due to its hardness and strength.

NIMONIC 75

Nimonic 75 (UNS N06075) is a versatile nickel-chromium alloy with excellent high-temperature strength and oxidation resistance. The specifications AMS 5754 and ASTM B435 highlight its use in components that must endure severe operating conditions, including turbine blades and other critical engine parts.

Composition
  • Carbon (C): Min 0.08%, Max 0.15%
  • Manganese (Mn): Max 1.00%
  • Silicon (Si): Max 1.00%
  • Chromium (Cr): Min 18.0%, Max 21.0%
  • Titanium (Ti): Min 0.2%, Max 0.6%
  • Copper (Cu): Max 0.5%
  • Iron (Fe): Max 0.5%
  • Nickel (Ni): Remainder
Properties
  • Density: Approximately 8.5 g/cm³.
  • Thermal Conductivity: ~12 W/m·K.
  • Tensile Strength: High tensile strength at elevated temperatures.
  • Creep Resistance: Excellent creep resistance at high temperatures.
Applications
  • NIMONIC 75 is extensively used in aerospace for turbine blades, engine components, and exhaust systems, where its high-temperature resistance and strength.
Advantages
  • High Temperature Strength: Retains strength and stability under extreme temperatures.
  • Excellent Creep Resistance: Performs well under prolonged exposure to high temperatures and stress.
Limitations
  • Cost: Relatively high cost due to the alloy's composition and processing requirements.
  • Machinability: Can be challenging to machine due to its hardness and strength.

INCONEL 909

Inconel 909 (UNS N19909) is characterized by its high strength and oxidation resistance at elevated temperatures. With specifications AMS 5759 and ASTM B462, it is particularly well-suited for applications in aerospace and gas turbine engines where high-temperature stability and performance are crucial.

Composition
  • Carbon (C): Max 0.060%
  • Nickel (Ni): Min 35.000%, Max 40.000%
  • Silicon (Si): Min 0.250%, Max 0.500%
  • Cobalt (Co): Min 12.000%, Max 16.000%
  • Niobium (Nb): Min 4.300%, Max 5.300%
  • Titanium (Ti): Min 1.300%, Max 1.800%
  • Iron (Fe): Balance
Properties
  • Density: Approximately 8.4 g/cm³.
  • Thermal Conductivity: ~12 W/m·K.
  • Tensile Strength: Excellent tensile strength at elevated temperatures.
  • Oxidation Resistance: Good resistance to oxidation and carburization.
Applications
  • INCONEL 909 is used in aerospace applications for turbine blades, engine components, and exhaust systems due to its high-temperature strength and oxidation resistance.
Advantages
  • High Strength: Maintains high mechanical strength and stability under extreme temperatures.
  • Good Oxidation Resistance: Performs well in oxidizing environments and at high temperatures.
Limitations
  • Cost: High cost due to the alloy's composition and processing requirements.
  • Machinability: Can be challenging to machine due to its hardness and strength.

INCONEL 718

Inconel 718 (UNS N07718) is a widely used nickel-chromium alloy noted for its excellent strength, fatigue resistance, and ability to withstand high temperatures. Specified under AMS 5662 and ASTM B637, it finds extensive use in aerospace and power generation due to its reliability and durability in harsh environments.

Composition
  • Carbon (C): Max 0.08%
  • Manganese (Mn): Max 0.35%
  • Silicon (Si): Max 0.35%
  • Phosphorus (P): Max 0.015%
  • Sulfur (S): Max 0.015%
  • Nickel (Ni): Min 50.0%, Max 55.0%
  • Molybdenum (Mo): Min 2.80%, Max 3.30%
  • Chromium (Cr): Min 17.0%, Max 21.0%
  • Titanium (Ti): Min 0.65%, Max 1.15%
  • Aluminum (Al): Min 0.20%, Max 0.80%
  • Cobalt (Co): Max 1.00%
  • Boron (B): Max 0.006%
  • Copper (Cu): Max 0.30%
  • Iron (Fe): Balance
Properties
  • Density: Approximately 8.19 g/cm³.
  • Thermal Conductivity: ~11 W/m·K.
  • Tensile Strength: High tensile strength at elevated temperatures.
  • Oxidation Resistance: Excellent.
Applications
  • INCONEL 718 is extensively used in aerospace applications, including turbine engines, structural components, and exhaust systems due to its high strength.
Advantages
  • High-Temperature Strength: Maintains strength at elevated temperatures.
  • Corrosion Resistance: Excellent resistance to oxidation and corrosion.
Limitations
  • Cost: High cost due to complex composition.
  • Machinability: Difficult to machine.

INCONEL 660 (A-286)

Inconel 660 (A-286) (UNS S66826) is a high-strength, age-hardenable alloy with excellent resistance to oxidation and creep at elevated temperatures. Specifications such as ASTM A453 and AMS 5731 underscore its suitability for demanding applications in aerospace and high-temperature industrial processes, providing a balance of strength and resistance in extreme environments.

Composition
  • Carbon (C): Max 0.040%
  • Manganese (Mn): Max 1.0%
  • Silicon (Si): Max 0.50%
  • Phosphorus (P): Max 0.020%
  • Sulfur (S): Max 0.015%
  • Nickel (Ni): Max 25.5%
  • Iron (Fe): Max 54.0%
  • Chromium (Cr): Max 14.8%
  • Titanium (Ti): Max 2.13%
  • Molybdenum (Mo): Max 1.30%
  • Vanadium (V): Max 0.30%
  • Aluminum (Al): Max 0.18%
  • Boron (B): Max 0.0060%
Properties
  • Density: Approximately 8.0 g/cm³.
  • Thermal Conductivity: ~15 W/m·K.
  • Tensile Strength: High tensile strength at high temperatures.
  • Oxidation Resistance: Good.
Applications
  • INCONEL 660 is used in aerospace applications for turbine blades, exhaust systems, and other components where high strength and resistance to high temperatures are crucial.
Advantages
  • High Strength: Maintains high strength at elevated temperatures.
  • Good Oxidation Resistance: Performs well in oxidizing environments.
Limitations
  • Cost: Expensive due to the alloy's composition.
  • Machinability: Challenging to machine.

NICKEL BASED ALLOYS

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