Haynes R-41 alloy,UNS N07041, AMS 5545, AMS 5712，1

### Technical Datasheet: Haynes® R-41® Alloy (UNS N07041) **Classification:** Nickel-Based, Gamma-Prime (γ') Strengthened Superalloy **Common Names:** R-41, Alloy R-41, Haynes R-41 **Specifications:** UNS N07041, AMS 5545, AMS 5712 --- #### 1.0 Introduction **Haynes® R-41®** is a high-strength, precipitation-hardenable nickel-chromium-cobalt superalloy renowned for its exceptional high-temperature capabilities. Developed primarily for aerospace applications, this alloy achieves its outstanding properties through a high volume fraction of gamma prime (γ') precipitates within its austenitic matrix. R-41 exhibits **excellent creep rupture strength, superior oxidation resistance, and remarkable thermal stability** at temperatures up to 1800°F (980°C), making it particularly suitable for the most demanding gas turbine engine components. --- #### 2.0 Chemical Composition (Weight %) | Element | Minimum | Maximum | Typical Value | Key Function | |---------|---------|---------|---------------|--------------| | **Nickel (Ni)** | Balance | Balance | ~55% | Austenitic matrix formation | | **Chromium (Cr)** | 18.0 | 20.0 | 19.0 | Oxidation & hot corrosion resistance | | **Cobalt (Co)** | 10.0 | 12.0 | 11.0 | Solid-solution strengthening | | **Molybdenum (Mo)** | 9.0 | 10.5 | 9.8 | Solid-solution strengthening | | **Titanium (Ti)** | 3.0 | 3.5 | 3.1 | Primary gamma' former (Ni₃Ti) | | **Aluminum (Al)** | 1.4 | 1.7 | 1.5 | Gamma' former (Ni₃Al) | | **Iron (Fe)** | - | 1.0 | 0.5 | - | | **Carbon (C)** | 0.05 | 0.10 | 0.07 | Carbide formation for grain boundary strength | | **Boron (B)** | 0.003 | 0.010 | 0.006 | Grain boundary strengthening | | **Zirconium (Zr)** | - | 0.07 | 0.03 | Grain boundary stabilization | --- #### 3.0 Physical Properties | Property | Value | Condition/Notes | |----------|-------|-----------------| | **Density** | 8.27 g/cm³ (0.299 lb/in³) | At room temperature | | **Melting Range** | 1305-1365°C (2380-2490°F) | - | | **Thermal Expansion Coefficient** | 12.6 μm/m·°C | 20-100°C | | **Thermal Conductivity** | 11.2 W/m·K | At 100°C | | **Electrical Resistivity** | 132 μΩ·cm | At room temperature | | **Modulus of Elasticity** | 214 GPa (31.0×10⁶ psi) | At room temperature | | **Specific Heat** | 440 J/kg·K | At 20°C | --- #### 4.0 Mechanical Properties **4.1 Room Temperature Properties (Heat Treated Condition):** - **Tensile Strength**: 1310-1520 MPa (190-220 ksi) - **Yield Strength (0.2% Offset)**: 1030-1240 MPa (150-180 ksi) - **Elongation**: 10-20% - **Reduction of Area**: 12-25% **4.2 Elevated Temperature Properties:** | Temperature | Tensile Strength | Yield Strength (0.2% Offset) | Creep Rupture Strength (1000h) | |-------------|------------------|-----------------------------|-------------------------------| | 1200°F (650°C) | 1035 MPa (150 ksi) | 895 MPa (130 ksi) | 310 MPa (45 ksi) | | 1400°F (760°C) | 895 MPa (130 ksi) | 760 MPa (110 ksi) | 170 MPa (25 ksi) | | 1600°F (870°C) | 620 MPa (90 ksi) | 550 MPa (80 ksi) | 70 MPa (10 ksi) | --- #### 5.0 Heat Treatment **Standard Heat Treatment Cycle:** 1. **Solution Treatment**: 2100-2150°F (1150-1180°C) for 2 hours, air cool 2. **Primary Aging**: 1550°F (845°C) for 4-8 hours, air cool 3. **Secondary Aging**: 1400°F (760°C) for 16 hours, air cool *Note: Specific heat treatment parameters may vary based on product form and application requirements.* --- #### 6.0 Key Characteristics & Applications **6.1 Key Characteristics:** - **Exceptional High-Temperature Strength**: Superior creep rupture strength up to 980°C (1800°F) - **Excellent Oxidation Resistance**: Good resistance to scaling and oxidation in air - **Thermal Stability**: Maintains microstructural stability during long-term exposure - **Good Fatigue Resistance**: Suitable for cyclic loading applications - **Moderate Weldability**: Can be welded using matching filler metals with proper precautions **6.2 Primary Applications:** - **Aerospace Gas Turbine Components**: - Turbine blades and vanes - Combustion chambers and afterburner components - Turbine disks and shafts - **Industrial Gas Turbines**: - Buckets (blades) and nozzles - Hot section stationary components - **Rocket Engine Components**: - Nozzle sections and thrust chambers --- #### 7.0 Fabrication & Processing **7.1 Manufacturing Processes:** - Hot working: Forging, rolling, and extrusion at 1800-2150°F (980-1180°C) - Cold working: Limited due to high strength - Machining: Requires rigid equipment and positive feeds - Welding: Gas tungsten arc welding (GTAW) with R-41 filler metal **7.2 Processing Considerations:** - Susceptible to strain-age cracking during welding and heat treatment - Requires controlled cooling rates after solution treatment - Sensitive to notches and stress concentrations - Post-weld heat treatment generally required --- #### 8.0 International Standards & Specifications **Primary Specifications:** | Standard Organization | Standard Number | Description | |----------------------|-----------------|-------------| | **Aerospace Material Specification** | AMS 5545 | Sheet, Strip, and Plate | | **Aerospace Material Specification** | AMS 5712 | Bars, Forgings, and Rings | | **Unified Numbering System** | UNS N07041 | Material Designation | | **ASTM International** | ASTM B637 | Nickel-Based Superalloy Bar & Billet | **Additional International Standards:** - **European**: DIN 2.4950 (similar composition alloys) - **Aerospace Manufacturer Specifications**: Various engine manufacturer specifications --- #### 9.0 Quality Assurance & Testing **Standard Testing Requirements:** - Chemical analysis verification - Mechanical property testing at room and elevated temperatures - Microstructural examination - Non-destructive testing (ultrasonic, penetrant) - Creep and stress rupture testing for critical applications --- **Note:** Haynes® and R-41® are registered trademarks of Haynes International, Inc. This alloy represents a premium high-temperature material solution for critical aerospace applications where maximum temperature capability and strength are required. Due to its complex composition and processing requirements, consultation with the manufacturer and thorough testing under actual service conditions are strongly recommended for all critical applications. The alloy's performance makes it particularly valuable in advanced gas turbine engines where operating temperatures continue to increase for improved efficiency.

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 3283 gallon liquid totes Special package is available on request.