Jan 20, 2026 Leave a message

ASTM B168/AMS 5542/Uns N07750 Nickel Alloy Tube For Jet Engine Parts Inconel X-750 Super Alloy Pipe

1. Question: What are the main applications of these alloys?


Answer:

ASTM B168/AMS 5542/UNS N07750 Nickel Alloy Tube: Primarily used in aerospace and jet engine components due to excellent high-temperature strength and corrosion resistance.

Inconel X-750 Super Alloy Pipe: Commonly used in turbine blades, fasteners, and high-temperature structural parts in aerospace and power generation industries.

 


2. Question: What are the typical mechanical and thermal properties?


Answer:

Nickel Alloy Tube (UNS N07750):

Tensile strength: ~1035 MPa

Good creep-rupture resistance at temperatures up to 700°C

Excellent resistance to oxidation and high-temperature corrosion

Inconel X-750 Pipe:

Tensile strength: ~1100 MPa

Can maintain strength at temperatures up to 700–760°C

Excellent stress-rupture and fatigue resistance

 


3. Question: What sizes and forms are typically available?


Answer:

Nickel Alloy Tube: Available in OD 6–100 mm, wall thickness 1–10 mm, lengths up to 6 meters; can be supplied seamless or welded.

Inconel X-750 Pipe: Typically available in OD 10–200 mm, wall thickness 2–20 mm, standard lengths 6 meters, can also be customized.

 


4. Question: How do these alloys perform in corrosive or high-temperature environments?


Answer:

Both alloys have excellent resistance to oxidation, carburization, and chloride-induced stress corrosion cracking.

Suitable for high-temperature gas turbines, exhaust systems, and chemical processing applications.

Can withstand prolonged operation in oxidizing and mildly reducing environments without significant degradation.

 


5. Question: Are there any special processing or heat treatment requirements?


Answer:

Nickel Alloy Tube (UNS N07750): Solution annealed at 980–1020°C, followed by water or air cooling; stress relief may be required after welding.

Inconel X-750 Pipe: Precipitation-hardened through solution annealing at 980–1020°C, aging at 715–760°C; recommended for maintaining high strength and fatigue resistance.

Both alloys may require precision machining and surface finishing for aerospace applications.

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