NIMONIC Alloy 115,BS HR4; Werkstoff Nr. 2.4636; 1

### **Product Introduction: NIMONIC® Alloy 115** **NIMONIC® Alloy 115** is a premium-grade precipitation-hardenable nickel-chromium-cobalt superalloy that represents one of the most advanced members of the Nimonic series. This alloy is specifically engineered for exceptional high-temperature performance in the most demanding aerospace applications, offering superior creep resistance, excellent oxidation stability, and outstanding mechanical properties at temperatures up to 1050°C (1922°F). The alloy's exceptional properties are achieved through an advanced combination of solid-solution strengthening and gamma prime (γ') precipitation hardening, with carefully optimized additions of cobalt, titanium, and aluminum that create a highly stable microstructure capable of withstanding extreme thermal and mechanical stresses for prolonged durations. --- ### **Chemical Composition** The chemical composition is precisely formulated to maximize high-temperature performance and microstructural stability: | Element | Content (%) | | :--- | :--- | | **Nickel (Ni)** | Balance | | **Chromium (Cr)** | 14.0 - 16.0 | | **Cobalt (Co)** | 13.0 - 16.0 | | **Aluminum (Al)** | 4.8 - 5.5 | | **Titanium (Ti)** | 3.5 - 4.5 | | **Molybdenum (Mo)** | 3.0 - 4.0 | | **Iron (Fe)** | 1.0 max | | **Carbon (C)** | 0.15 - 0.25 | | **Silicon (Si)** | 0.5 max | | **Manganese (Mn)** | 0.5 max | | **Boron (B)** | 0.01 - 0.03 | | **Zirconium (Zr)** | 0.05 - 0.15 | --- ### **Physical Properties** Nimonic Alloy 115 exhibits superior physical characteristics for extreme temperature service: | Property | Value | | :--- | :--- | | **Density** | 8.05 g/cm³ | | **Melting Point** | 1330-1380 °C | | **Thermal Conductivity** | 11.5 W/m·K (at 20°C) | | **Electrical Resistivity** | 1.38 μΩ·m | | **Modulus of Elasticity** | 232 GPa (at 20°C) | | **Coefficient of Thermal Expansion** | 13.8 μm/m·°C (20-900°C) | | **Specific Heat Capacity** | 455 J/kg·K | | **Magnetic Permeability** | <1.01 | --- ### **Mechanical Properties** The alloy demonstrates exceptional high-temperature mechanical performance: **Room Temperature Properties (Fully Heat Treated):** - **Tensile Strength:** 1350-1550 MPa - **Yield Strength (0.2% Offset):** 1000-1200 MPa - **Elongation:** 10-18% - **Reduction of Area:** 15-25% - **Hardness:** 40-48 HRC **High-Temperature Performance:** - **Creep Rupture Strength (950°C/100h):** 150 MPa - **Fatigue Strength (850°C):** 280 MPa - **Stress Rupture Life (950°C/150MPa):** >100 hours --- ### **Heat Treatment** **Solution Treatment:** - Temperature: 1190-1210°C - Soaking Time: 2-4 hours - Cooling: Rapid air cooling or forced air quenching **Precipitation Hardening:** - Primary Aging: 1050-1080°C for 4-8 hours, air cool - Secondary Aging: 800-850°C for 16-24 hours, air cool --- ### **Key Characteristics & Advantages** 1. **Exceptional High-Temperature Capability** - Maintains mechanical properties up to 1050°C - Superior creep and stress rupture resistance - Excellent thermal fatigue performance 2. **Outstanding Microstructural Stability** - Highly resistant to phase transformation and coarsening - Maintains properties during extended high-temperature exposure - Excellent resistance to thermal aging effects 3. **Superior Environmental Resistance** - Excellent oxidation resistance up to 1150°C - Outstanding resistance to hot corrosion - Stable protective oxide layer formation 4. **Advanced Manufacturing Characteristics** - Suitable for precision investment casting - Requires specialized hot working techniques - Demands advanced machining approaches --- ### **Product Applications** **Aerospace Industry:** - High-pressure turbine blades and vanes - Turbine disks and rotors - Combustion chamber components - Afterburner components - Exhaust system structural parts **Power Generation:** - Industrial gas turbine blades - Turbine disks and shafts - High-temperature structural components - Combustion system parts **Specialized Applications:** - Rocket engine components - Nuclear reactor core components - High-temperature test fixtures - Specialized high-temperature tooling --- ### **International Standards** Nimonic Alloy 115 conforms to major international aerospace specifications: | Standard Type | Standard Number | Description | | :--- | :--- | :--- | | **BS** | HR4 | British Standard | | **Werkstoff** | 2.4636 | Material Number | | **AFNOR** | NCK 15 ATD | French Standard | | **AECMA** | Pr EN 2196, 2197 | European Aerospace Standard | --- ### **Summary** **NIMONIC Alloy 115** represents the pinnacle of nickel-chromium superalloy technology, offering unmatched high-temperature performance for the most demanding aerospace applications. Its advanced composition, featuring optimized cobalt, titanium, and aluminum content combined with precise control of precipitation hardening elements, provides exceptional creep resistance, microstructural stability, and oxidation resistance at temperatures approaching 1050°C. The alloy's capability to maintain mechanical integrity under extreme thermal and mechanical conditions makes it indispensable for critical rotating components in advanced gas turbine engines, where reliability and performance are paramount. Compliance with multiple stringent international standards including BS HR4, Werkstoff 2.4636, and AECMA Pr EN 2196-2197 ensures consistent quality and performance across global aerospace applications, providing confidence for engineers designing next-generation propulsion systems operating at the frontiers of temperature and performance limits.

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 3317 gallon liquid totes Special package is available on request.