718Plus Nickel Superalloy,UNS N07818,Allvac 718Plus alloy (UNS N07818),E FORU

**Product Overview: 718Plus® Nickel Superalloy (UNS N07818)** **718Plus®** (UNS N07818), also known as **Allvac® 718Plus**, is an advanced precipitation-hardenable nickel-based superalloy developed to bridge the performance gap between conventional Alloy 718 and more expensive higher-temperature superalloys. This innovative alloy offers approximately 55°C (100°F) higher temperature capability than standard 718 while maintaining similar processing characteristics and excellent fabricability. --- ### **Key Characteristics & Advantages** - **Enhanced Temperature Capability**: 55°C (100°F) higher operating temperature than Alloy 718 - **Excellent Thermal Stability**: Maintains microstructural stability up to 704°C (1300°F) - **Superior Strength Retention**: Better strength retention at elevated temperatures compared to 718 - **Good Fabricability**: Similar workability and weldability to Alloy 718 - **Excellent Corrosion Resistance**: Comparable oxidation resistance to Alloy 718 - **Cost-Effective Performance**: Bridges gap between 718 and more expensive superalloys --- ### **Chemical Composition (Typical Weight %)** | Element | Content Range (%) | Function Description | |------------------|-------------------|-----------------------| | **Nickel (Ni)** | Balance | Base element providing austenitic matrix | | **Chromium (Cr)**| 16.0-18.0 | Primary element for oxidation resistance | | **Iron (Fe)** | 8.0-10.0 | Cost-effective strengthening element | | **Cobalt (Co)** | 8.0-10.0 | Enhances high-temperature stability | | **Molybdenum (Mo)**| 2.50-3.30 | Solid solution strengthener | | **Tungsten (W)** | 0.90-1.30 | Enhances high-temperature strength | | **Niobium (Nb)** | 5.20-5.80 | Forms γ'' strengthening phase | | **Aluminum (Al)**| 1.20-1.60 | Forms γ' precipitation hardening phase | | **Titanium (Ti)**| 0.70-1.20 | Contributes to γ' precipitation | | **Carbon (C)** | ≤0.03 | Controlled for carbide formation | | **Boron (B)** | 0.004-0.009 | Enhances grain boundary strength | --- ### **Physical Properties** | Property | Typical Value | Test Conditions | |---------------------------------|------------------------|--------------------------| | **Density** | 8.26 g/cm³ | At room temperature | | **Melting Range** | 1255-1345°C | Solidus-Liquidus | | **Thermal Expansion Coefficient**| 13.5 × 10⁻⁶/°C | 20-600°C range | | **Thermal Conductivity** | 12.8 W/m·K | At 700°C | | **Specific Heat Capacity** | 440 J/kg·K | At 700°C | | **Electrical Resistivity** | 1.28 μΩ·m | At 20°C | | **Young's Modulus** | 205 GPa | At room temperature | --- ### **Mechanical Properties** #### **Solution Treated and Aged Condition** | Property | Temperature | Typical Value | |------------------------|-------------|----------------------| | **Tensile Strength** | 20°C | 1450 MPa | | **Tensile Strength** | 704°C | 1035 MPa | | **Yield Strength (0.2%)** | 20°C | 1240 MPa | | **Yield Strength (0.2%)** | 704°C | 930 MPa | | **Elongation** | 20°C | 15% | | **Elongation** | 704°C | 14% | | **Reduction of Area** | 20°C | 18% | | **Creep Rupture Life** | 704°C/517 MPa | 50 hours | --- ### **Heat Treatment** Standard heat treatment sequence includes: - **Solution Treatment**: 954-982°C (1750-1800°F) for 1 hour, air cool - **Aging Treatment**: 788°C (1450°F) for 8 hours, furnace cool to 704°C (1300°F) at 55°C/hour - **Hold at 704°C**: 8 hours total aging time, air cool --- ### **International Standards & Specifications** 718Plus® complies with the following international standards: - **AMS 5999**: Wrought Alloy 718Plus - **ASTM B637**: Precipitation Hardening Nickel Alloy Bars, Forgings, and Forging Stock - **GE Specification**: GE A50 TF 33 / GE S1A 718Plus - **Pratt & Whitney**: PWA 1286 - **Rolls-Royce**: RRS 70004 - **SNECMA**: Specification for Aerospace Applications --- ### **Applications** 1. **Aerospace Gas Turbine Engines**: - High-pressure turbine disks - Compressor disks and spools - Turbine blades and vanes - Combustion chamber components - Afterburner parts 2. **Industrial Gas Turbines**: - Power generation turbine components - Hot gas path parts - Turbine wheels and disks - High-temperature fasteners 3. **High-Temperature Structural Components**: - Rocket engine components - Nuclear reactor parts - High-stress fasteners - Specialized industrial equipment --- ### **Manufacturing Considerations** - **Forging**: Hot workable in temperature range 950-1120°C - **Machining**: Similar machinability to Alloy 718 - **Welding**: Excellent weldability using matching filler metals - **Heat Treatment**: Requires precise control of time-temperature parameters - **Quality Control**: Stringent NDT requirements including ultrasonic inspection --- ### **Available Forms** - **Bar and Rod**: Various diameters and lengths - **Forgings**: Custom shapes and sizes - **Billet**: For subsequent manufacturing operations - **Sheet and Plate**: For structural applications - **Fasteners**: High-temperature bolts and nuts --- **Disclaimer**: *The information provided is for technical reference purposes only. 718Plus® is a registered trademark of ATI Specialty Materials. This specialized superalloy requires proper processing and heat treatment to achieve specified properties. Actual performance may vary depending on manufacturing processes, heat treatment parameters, and specific application conditions. Users should consult with qualified materials engineers and adhere to OEM specifications for critical applications. All manufacturing and processing should follow approved procedures and quality standards.*

Packing of Standard Packing: Typical bulk packaging includes palletized plastic 5 gallon/25 kg. pails, fiber and steel drums to 1 ton super sacks in full container (FCL) or truck load (T/L) quantities. Research and sample quantities and hygroscopic, oxidizing or other air sensitive materials may be packaged under argon or vacuum. Solutions are packaged in polypropylene, plastic or glass jars up to palletized 3125 gallon liquid totes Special package is available on request.