Alloy 718 Round Bar, Plate, Sheet and Coil - AMS 5596, 5662, N07718
Inconel® 718 is a precipitation-hardening nickel-chromium alloy containing significant amounts of iron, columbium, and molybdenum, along with lesser amounts of aluminum and titanium. This alloy has relatively good weldability, formability, and excellent cryogenic properties compared to other precipitation hardening nickel alloys. Inconel® Alloy 718 is non-magnetic. It maintains good corrosion resistance and oxidation resistance and is used for parts requiring high resistance to creep and stress rupture up to 1300°F (704°C) and oxidation resistance up to 1800°F (982°C). 718 material maintain high strength and good ductility up to 1300°F (704°C).
- Inventory & Specs
- Chemical Composition
- Physical Properties
- Mechanical Properties
- Datasheet
- Additional Info
Inventory Size Ranges for 718
| Type | Thickness | AMS Standards | ASTM | UNS | ASME | Get a Quote |
|---|---|---|---|---|---|---|
| Coil | 0.020" - 0.160" | AMS 5596 | ASTM B 670 | UNS N07718 | ASME SB 670 | Get a Quote |
| Sheet | 0.020" - 0.160" | AMS 5596 | ASTM B 670 | UNS N07718 | ASME SB 670 | Get a Quote |
| Plate | 0.1875" - 2.000" | AMS 5596 | ASTM B 670 | UNS N07718 | ASME SB 670 | Get a Quote |
| Bar | 0.250" - 10.000" | AMS 5662 | ASTM B 637 | UNS N07718 | Get a Quote | |
| Precision Reroll Strip | 0.0008" - 0.015" | Get a Quote |
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Advanced Inventory Size Ranges for 718
| Type | Thickness | Get a Quote |
|---|---|---|
| Powder | Get a Quote | |
| Build Plates | Get a Quote | |
| Feedstock | Get a Quote |
Characteristics of Inconel 718
This material features excellent tensile and impact strength. Type 718 alloy has good resistance to oxidation and corrosion at temperatures in the alloy’s useful strength range in atmospheres encountered in jet engines and gas turbine operators.
Working with Inconel 718
718 permits repair welding even in the aged condition. It is generally supplied in the solution treated condition. The sluggish precipitation hardening response of this alloy allows it to be readily welded without hardening or cracking.
Other industry standards we comply with:
- PWA-LCS
- DFARS Compliant
- RR SABRe Edition 2
- GE Aircraft Engine (GT193)
- GE Aviation S-SPEC-35 AeDMS S-400
- EN 2.4668
- EN 10204
Common Trade Names
- Haynes 718 (® Haynes International)
- ATI 718 (â„¢ Allegheny Technologies)
- Inconel Alloy 718 (® Special Metals)
- INCONEL® Alloy 718 (Haynes)
Industry Applications for 718
- Jet engine
- Gas turbine operations
- Base plates
- Rotor bolts (Power generation)
- Burst discs
Chemical Composition
| Element | Min | Max | |
|---|---|---|---|
| C | Carbon | - | 0.008 |
| Mn | Manganese | - | 0.35 |
| P | Phosphorus | - | 0.015 |
| S | Sulfur | - | 0.015 |
| Si | Silicon | - | 0.35 |
| Cr | Chromium | 17.00 | 21.00 |
| Ni | Nickel | 50.00 | 55.00 |
| Mo | Molybdenum | 2.80 | 3.30 |
| Nb | Columbium | 4.75 | 5.50 |
| Ti | Titanium | 0.65 | 1.15 |
| Al | Aluminum | 0.20 | 0.80 |
| Co | Cobalt | - | 1.00 |
| B | Boron | - | 0.006 |
| Cu | Copper | - | 0.30 |
| Ta | Tantalum | - | 0.05 |
| Fe | Iron | - | Balance |
Physical Properties
- Electrical Resistivity at 68°F (20°C)
- Annealed: 127 microhm-cm
- Aged: 121 microhm-cm
| Property | Annealed Condition | Aged Condition |
|---|---|---|
| Density | 0.296 lb./in3 (8.19 g/cm3) | 0.297 lb./in3 (8.22 g/cm3) |
| Specific Gravity | 8.19 | 8.22 |
| Temperature Range | Coefficients | ||
|---|---|---|---|
| °C | °F | W/m·K | Btu/(hr/ft²/in/°F) |
| 0-100 | 32-212 | 6.5 | 11.2 |
Mechanical Properties
Typical Short Time Tensile Properties as a Function of Temperature
- Solution Treatment: 1800°F (982°C) 1 hour
- Precipitation Treatment: 1325°F (718°C) 8 hours, Furnace Cool at 100°F (55°C) per hour to 1150°F (621°C) 8 hours
Inconel 718 machining often results in less tool life due to the work hardening and abrasion properties of the alloy. High cutting pressure and temperature also contributes towards work hardening, surface tearing, and deformation.
| Product | Yield Strength Max (0.2% offset) | Ultimate Tensile Strength Max | Elongation (% in 2") |
|---|---|---|---|
| Sheet & Strip | 80,000 psi (550 MPa) | 14,000 (965 MPa) | 30 (min) |
| Plate | 105,000 psi (725 MPa) | 150,000 (1,035 MPa) | 30 (min) |
| Yield Strength Max (0.2% offset) | Ultimate Tensile Strength Min | Elongation (% in 2") |
|---|---|---|
| 150,000 (1,035 MPa) | 180,000 (1,240 MPa) | 12 (min) |
Additional Info
A brief history of Inconel 718
Inconel 718® is a modern superalloy, first patented on July 24th, 1962. The creation of this alloy was a direct offshoot of nearly a decade of research to create a Nickel Chromium Molybdenum Niobium (Ni-Cr-Mo) superalloy – Inconel 625. After World War II, the term "superalloy" was coined to describe alloys designed for turbines and superchargers that required high performance at extreme temperatures. The original inspiration for this work was a novel, high-strength material used in steam lining for pipes carrying pressurized steam in power plants. Today, Inconel® 718 is one of the most widely used alloys in the aerospace industry, heavily featured in engines, turbines, and heat exchangers.
How was Inconel® 718 created?
In the 1950s, there was an anticipated demand for a material for steam lines in power plants that could carry steam at supercritical pressures. Goals for product characteristics amounted to ease of weldability, workable into tubing, creep resistance, and non age-hardening material. From prior work with single alloys using commonly alloyed materials like titanium and chromium, researchers knew an advanced combination of elements would be needed to form an alloy matrix with the necessary properties.
The research that led to the creation and patenting of Inconel® 718 stemmed from research to develop 625. The failure of samples after a simple age hardening test spurred the creation of 718 - a superalloy with high strength, good weldability, and the ability to be fabricated in a variety of shapes and forms.
What were the first applications of this superalloy?
Initial processing of nickel alloy 718 was difficult compared to today, with vacuum processing an early and unrefined technology. This led to a product that was not nearly as uniform as modern production, but the unique properties of this alloy made it very desirable, as it could replace complex welded assemblies with castings while remaining highly weldable.
In 1963, the diffuser case for the Blackbird SR-71’s J-58 engine was one of the very first applications of Inconel 718. It was capable of withstanding 1250 degrees F, making it ideal in jet engine applications like the advanced design of the SR-71.
How is Inconel® 718 used today?
This grade of Inconel® accounts for roughly half of the production of superalloys today and is widely used in power industries due to its high-stress resistance at temperatures found in gas turbines. It is so prevalent in these applications that around 30% of the weight of a typical engine comes from alloy 718. It is used in compressor blades and vanes, shafts, supports cases, and more.
Almost half of the 718 nickel alloy produced today is used in aerospace applications like aircraft and rocket engines, for many essential components like blades and sheets. This superalloy excels at a range of temperatures while maintaining creep resistance, corrosion resistance, tensile strength, and yield strength that prevents stress fractures in common operating conditions. The strong toughness at low temperatures that makes it ideal for spacecraft also makes it perfect for cryogenic applications, such as storage containers for liquid nitrogen held at -196 degrees F.
More information about your 718 supplier
United Performance Metals is your global specialty metals solutions center providing alloy 718 in round bar, plate, and sheet formulations, and we have supplied many large (and smaller) names in the aerospace and power industries. Give us a call to find out what we can do for you.