AMS 5662 Certified Inconel 718 Alloy Plate For Jet Engines & Gas Turbines

AMS 5662 Certified Inconel 718 Alloy Plate For Jet Engines & Gas Turbines

Products Specification

AMS 5662 Certified Inconel 718 Alloy Plate – Engineered for Jet Engines & Gas Turbines

When performance, reliability, and safety are non-negotiable—as in aerospace propulsion systems—the choice of material is critical. AMS 5662 certified Inconel 718 alloy plate is the industry-standard solution for high-stress, high-temperature components in jet engines, industrial gas turbines, and auxiliary power units (APUs). Backed by rigorous aerospace material specifications and precision metallurgical control, this nickel-chromium superalloy delivers unmatched strength, creep resistance, and oxidation stability from cryogenic temperatures up to 704°C (1300°F).

This comprehensive product overview details the composition, certification, mechanical properties, applications, and advantages of AMS 5662-compliant Inconel 718 plate, tailored for the most demanding turbine environments.

What Is AMS 5662?

AMS 5662 is an Aerospace Material Specification published by SAE International that defines the requirements for precipitation-hardened Inconel 718 in the form of bars, forgings, and plate used in rotating and static engine components. Compliance with AMS 5662 ensures:

• Strict chemical composition limits
• Controlled heat treatment (solution annealing + double aging)
• Verified mechanical properties at room and elevated temperatures
• Mandatory ultrasonic inspection for internal integrity
• Full traceability and documentation per AS9100 quality standards

AMS 5662 is widely specified by OEMs such as Pratt & Whitney, GE Aviation, Rolls-Royce, and Safran for critical rotating parts where fatigue and creep resistance are paramount.

Why Inconel 718 for Turbine Applications?

Inconel 718 is a gamma-double-prime (γ″) strengthened nickel superalloy whose unique microstructure provides:

• Exceptional tensile and yield strength up to 700°C
• Outstanding fatigue and creep-rupture resistance under cyclic loading
• Stable performance during rapid thermal cycling
• Good fabricability and weldability without post-weld cracking
• Resistance to oxidation and hot corrosion in combustion zones

These attributes make it ideal for components exposed to extreme centrifugal forces, high-pressure gases, and aggressive exhaust environments.

Chemical Composition (Per AMS 5662)

Note: Nb is essential for forming γ″ (Ni₃Nb) precipitates during aging—the primary strengthening mechanism.

Heat Treatment (Per AMS 5662)

All AMS 5662 Inconel 718 plate undergoes a mandatory three-step thermal cycle:

1. Solution Anneal: 954–982°C (1750–1800°F), hold 1 hour, air cool
2. First Aging: 718°C (1325°F), hold 8 hours, furnace cool to 621°C (1150°F) at 56°C/hr (100°F/hr)
3. Second Aging: Hold at 621°C (1150°F) for 8 hours, then air cool

This double-aging process maximizes γ″ and γ′ precipitation, optimizing strength without compromising ductility.

Mechanical Properties (Minimum, Per AMS 5662)

Creep rupture life at 650°C / 690 MPa: ≥ 25 hours

These values are verified on every heat lot via tensile testing per ASTM E8/E21.

Ultrasonic Inspection (Mandatory per AMS 5662)

All plate must pass ultrasonic examination in accordance with AMS 2631 Class A or B (as specified):

• Detects internal flaws >1.6 mm (1/16") equivalent flat-bottom hole
• Ensures structural integrity for rotating components
• Reports include C-scan mapping for critical zones

This non-destructive testing is essential for flight-critical parts like turbine discs and spacers.

Typical Applications in Jet Engines & Gas Turbines

In industrial gas turbines, Inconel 718 is also used in combustion liners, transition pieces, and nozzle guide vanes.

Available Plate Specifications (AMS 5662 Compliant)

Material is supplied in the fully aged (H900 or H1075) condition unless otherwise requested.

Fabrication & Machining Considerations

• Machining: Use rigid setups, sharp carbide tools, low speeds (15–25 m/min), high feed rates, and ample coolant to counter work hardening.
• Grinding: Aluminum oxide or cubic boron nitride (CBN) wheels recommended.
• Drilling/Tapping: Pilot holes and slow RPMs prevent edge chipping.
• Non-Machinable Features: Complex geometries often start as near-net-shape forgings to reduce waste.

Note: Avoid cold working after final aging—this can induce residual stresses and reduce fatigue life.

Quality Assurance & Certification

Every AMS 5662 Inconel 718 plate shipment includes:

• Mill Test Report (MTR) with chemistry & mechanical data
• Heat treatment certification (time-temperature logs)
• Ultrasonic inspection report (per AMS 2631)
• AS9100 quality system compliance statement
• Optional: Nadcap accreditation for special processes

Full lot traceability from melt to delivery ensures compliance with FAA, EASA, and OEM audit requirements.

Conclusion

AMS 5662 certified Inconel 718 alloy plate is not just a material—it’s a flight-proven engineering solution trusted in millions of engine flight hours worldwide. Its combination of high-temperature strength, damage tolerance, and manufacturing consistency makes it irreplaceable in modern propulsion systems.

For aerospace manufacturers, maintenance providers, and Tier 1 suppliers, sourcing AMS 5662-compliant plate from a qualified supplier isn’t optional—it’s essential for safety, performance, and regulatory approval.