Inconel 751 Nickel Alloy Bar (UNS N07751,AMS 5667)
Inconel 751 is a precipitation-hardening nickel-based superalloy with the γ' phase (Ni₃(Al, Ti)) as the main strengthening phase. It maintains excellent strength, creep resistance, and fatigue resistance even at temperatures up to 870°C, while also exhibiting excellent resistance to gas corrosion and oxidation. Its primary applications are in aerospace engine components (such as turbine disks, blades, ring components, and fasteners), as well as industrial gas turbines and high-performance racing car power units.
Therefore, its price is extremely high, dozens of times that of ordinary stainless steel. Users pay for "high-temperature strength" and "aerospace quality." It is generally a custom-made material; aerospace-grade bars are not readily available. The MOQ is high, and lead times are typically 4-9 months, requiring planning and procurement.
Quality Inspection
Our quality inspection department conducts the following physical inspection procedures on every finished product:
1. Dimensions and Appearance:
We check the packaging of the inconel 751 alloy bars for integrity and surface quality to meet requirements. We randomly sample materials to verify that the diameter and length meet customer requirements, and perform a second inspection using different measuring tools (we have encountered situations where testing equipment had errors) to minimize measurement data errors.
2. Chemical Composition Verification (PMI):
We use a portable spectrometer to specifically verify the content of nickel, chromium, titanium, aluminum, and niobium. This is fundamental to preventing material mixing.
Hardness Testing (Quick and Effective): We measure the HRC hardness, which should be within the range of 28-35. This is a quick indication of acceptable performance.
Third-Party Authoritative Retesting (Crucial): For initial cooperation or major batches, samples must be sent to national-level aerospace materials testing institutions (such as the Beijing Institute of Aeronautical Materials or the China Aero Engine Testing Center) for full elemental analysis, room temperature/high temperature mechanical properties, creep/delay testing, and metallographic analysis. This is the only gold standard for verifying supplier data.
Chemical Composition
(Typical value, based on AMS 5667/5668)
|
Elements |
Content (%) |
|
Nickel, Ni |
≥ 70 |
|
Chromium, Cr |
14-17 |
|
Iron, Fe |
5-9 |
|
Titanium, Ti |
2-2.60 |
|
Aluminum, Al |
0.90-1.50 |
|
Niobium, Nb |
0.70-1.20 |
Note: Harmful impurities such as sulfur, phosphorus, lead, and bismuth must be strictly controlled, as they will deteriorate hot workability and high-temperature performance.
Physical Properties
|
Properties |
Metric |
Imperial |
|
Density |
8.22 g/cm³ |
0.297 lb/in³ |
|
Melting point |
1413°C |
2575°F |
Mechanical Properties
Standard time-sensitive status (e.g., AMS 5667 status)
|
Properties |
Metric |
Imperial |
|
Tensile Strength (precipitation hardened, value at room temperature) |
1275 MPa |
184900 psi |
|
Yield strength (at strain 200%, precipitation hardened, value at room temperature) |
875 MPa |
127000 psi |
|
Elongation at break (precipitation hardened) |
25% |
25% |
High-temperature durability (must be considered during procurement): For example, the fracture life under stress of 815°C/310 MPa is typically required to be ≥ 50 hours (the specific value depends on the technical specifications).
Key Procurement Points: You must clearly define the final delivery condition of the purchased bars. Is it "solution-annealed" for the user to heat-treat themselves, or "solution-treated and fully aged" for direct use? The aerospace industry typically requires the latter.
Processing difficulty and key points
Based on material data from past machining centers, Inconel 751 nickel alloy bars are notoriously difficult to machine due to their high strength and severe work hardening. Specialized tools, low-speed heavy cutting, and thorough cooling are required.
1. Heat treatment is crucial:
The heat treatment of Inconel 751 nickel alloy typically involves solution treatment at 1100-1150°C + intermediate treatment at 700-760°C + final aging at 600-650°C. This multi-stage heat treatment requires precise temperature and time control. This can be achieved using a vacuum furnace or protective atmosphere furnace with accurate temperature control and recording systems.
2. Welding requires extreme caution:
Due to its poor weldability, a complete post-weld heat treatment is necessary, and the process is complex. Welding should be avoided as much as possible in the design.
3. One-stop sourcing is strongly recommended:
For final products such as turbine disks and rings, forgings or finished products must be purchased directly from aerospace forging plants with full forging and heat treatment capabilities. Purchasing bars and then outsourcing completely compromises performance.
Hot Tags: Inconel 751, Nickel Alloy Bar, UNS N07751, AMS 5667 manufacturers, factory
You Might Also Like
Send Inquiry



