UDIMET alloy R41 Ni-Cr Alloy,UNS N07041; AMS 5545, 5712, 5713，1

### **Product Datasheet: UDIMET® Alloy R-41 (UNS N07041)** **A High-Strength, Precipitation-Hardenable Nickel-Chromium Superalloy** --- #### **1. Overview** UDIMET® Alloy R-41 is a high-performance, precipitation-hardenable **nickel-chromium superalloy** renowned for its exceptional **high-temperature strength**, **outstanding oxidation resistance** up to 980°C (1800°F), and excellent **creep-rupture properties**. It maintains a high strength level over a wide temperature range, making it a versatile and reliable material for the most demanding conditions in gas turbine engines. The alloy can be processed through conventional forming and welding techniques and is typically supplied in the solution-annealed condition. It achieves its remarkable mechanical properties through a precise aging treatment that precipitates a high volume fraction of the strengthening gamma prime (γ') phase. Its balanced properties have made it a standard material for high-pressure turbine stator and rotor components in both aerospace and industrial applications for decades. #### **2. Chemical Composition (Typical Weight %)** The composition is designed to create a robust oxide layer and a stable, strong microstructure. | Element | Content (%) | Role in the Alloy | | :--- | :--- | :--- | | **Nickel (Ni)** | Balance | Forms the austenitic matrix. | | **Chromium (Cr)** | ~19.0 | Provides superior oxidation and hot corrosion resistance. | | **Cobalt (Co)** | ~11.0 | Solid solution strengthener. | | **Molybdenum (Mo)** | ~10.0 | Potent solid solution strengthener. | | **Aluminum (Al)** | ~1.5 | Forms the primary strengthening γ' phase (Ni₃(Al,Ti)). | | **Titanium (Ti)** | ~3.1 | Forms the primary strengthening γ' phase (Ni₃(Al,Ti)). | | **Carbon (C)** | ~0.09 | Forms carbides for grain boundary strengthening. | | **Boron (B)** | ~0.005 | Enhances creep ductility and grain boundary strength. | | **Zirconium (Zr)** | ~0.07 | Further improves creep resistance. | | **Iron (Fe)** | ≤ 2.0 | Residual element. | #### **3. Physical Properties (Typical)** | Property | Value / Condition | | :--- | :--- | | **Density** | 8.27 g/cm³ (0.299 lb/in³) | | **Melting Range** | ~1290 - 1345 °C (~2350 - 2450 °F) | | **Thermal Expansion Coefficient** | ~13.9 μm/m·°C (20 - 540°C) | | **Thermal Conductivity** | ~13.0 W/m·K (at 100°C) | | **Modulus of Elasticity** | ~218 GPa (31.6 x 10⁶ psi) at 20°C | #### **4. Mechanical Properties** Properties are developed through a solution treatment followed by a two-stage aging process. The following are typical for material conforming to AMS 5712. **After Full Heat Treatment:** * **Tensile Strength:** > 1275 MPa (185 ksi) * **Yield Strength (0.2% Offset):** > 895 MPa (130 ksi) * **Elongation:** > 12% * **Reduction of Area:** > 15% **At Elevated Temperature (e.g., 815°C / 1500°F):** * **Tensile Strength:** ~690 MPa (100 ksi) * **0.2% Yield Strength:** ~620 MPa (90 ksi) * **Creep-Rupture Strength:** Excellent, capable of withstanding high stresses for extended periods at temperatures up to 980°C (1800°F). #### **5. Heat Treatment** UDIMET R-41 requires a specific multi-step heat treatment to achieve its optimal properties: 1. **Solution Treatment:** Heated to approximately 1180°C (2150°F), held, and then rapidly cooled (quenched). This dissolves the precipitates into the matrix. 2. **Aging Treatment:** A two-stage aging process is used (e.g., 1080°C / 1975°F for 4 hours, air cool, followed by 760°C / 1400°F for 16 hours, air cool) to precipitate a fine, uniform distribution of the γ' phase. #### **6. Product Applications** UDIMET R-41 is used in critical high-temperature components in aerospace and power generation, including: * **Turbine Blades and Vanes** (both stationary and rotating) * **Afterburner Components** * **Turbine Disks** * **Sheet Metal Combustion Parts** * **High-Temperature Fasteners and Bolts** #### **7. International and Industry Standards** UDIMET R-41 is covered by several key Aerospace Material Specifications (AMS), which define its requirements for different product forms. * **UNS:** **N07041** * **AMS:** * **AMS 5545:** Sheet, Strip, and Plate (Solution Heat Treated) * **AMS 5712:** Bars, Forgings, and Rings (Solution and Precipitation Heat Treated) * **AMS 5713:** Bars, Forgings, and Rings (Solution Heat Treated for Forging or Re-heat Treatment) * **Other:** It is also covered by various proprietary OEM specifications from manufacturers like GE Aviation and Pratt & Whitney. --- **Disclaimer:** The information provided is for technical reference and comparison purposes. Properties are typical and can vary with product form, heat treatment, and manufacturing process. For design and procurement, the official, latest issue of the relevant material specification (e.g., AMS 5545, 5712, 5713) must be consulted. UDIMET is a registered trademark of Special Metals Corporation (a PCC company).

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 3365 gallon liquid totes Special package is available on request.