Udimet 700 Nickel Alloy ,Nimonic 115; ATG W3，1

### **Technical Datasheet: A Comparison of High-Temperature Nickel-Based Superalloys** **Udimet® 700, Nimonic® 115, and ATG W3** --- ### **1. Udimet® 700 (UNS N07700)** #### **Overview** Udimet 700 is a high-strength, precipitation-hardenable nickel-based superalloy designed for extreme temperature service. It is renowned for its exceptional combination of high tensile and creep-rupture strength, good oxidation resistance, and microstructural stability up to approximately 980°C (1800°F). It is typically used in the most demanding rotating components in gas turbine engines. #### **Chemical Composition (Typical Weight %)** | Element | Content (%) | Role in the Alloy | | :--- | :--- | :--- | | **Nickel (Ni)** | Balance | Austenitic matrix. | | **Chromium (Cr)** | ~15.0 | Oxidation and hot corrosion resistance. | | **Cobalt (Co)** | ~18.5 | Solid solution strengthener. | | **Molybdenum (Mo)** | ~5.0 | Solid solution strengthener. | | **Aluminum (Al)** | ~4.3 | Forms the primary strengthening γ' phase (Ni₃Al). | | **Titanium (Ti)** | ~3.5 | Forms the primary strengthening γ' phase (Ni₃Ti). | | **Boron (B)** | ~0.025 | Grain boundary strengthener. | | **Carbon (C)** | ~0.07 | Forms carbides for grain boundary control. | #### **Physical & Mechanical Properties (Typical)** * **Density:** 7.92 g/cm³ * **Melting Range:** ~1290 - 1345 °C * **Room Temperature Tensile Strength (Aged):** Ultimate Tensile Strength (UTS) > 1275 MPa, Yield Strength (0.2% YS) > 1030 MPa. * **Key Feature:** Excellent creep strength at temperatures between 870°C and 980°C. #### **Product Applications** * Turbine blades and vanes * Turbine disks (forgings) * High-temperature fasteners and shafts #### **International Standards** * **AMS:** 5543 (Sheet, Strip, & Plate), 5757 (Forgings) * **UNS:** N07700 * **Werkstoff Nr.:** 2.4969 --- ### **2. Nimonic® 115** #### **Overview** Nimonic 115 is a nickel-chromium-cobalt superalloy strengthened by precipitation hardening. It was developed to offer superior creep-rupture strength compared to earlier Nimonic alloys, making it suitable for highly stressed components in the hot sections of turbines. It combines high strength with good oxidation resistance. #### **Chemical Composition (Typical Weight %)** | Element | Content (%) | Role in the Alloy | | :--- | :--- | :--- | | **Nickel (Ni)** | Balance | Austenitic matrix. | | **Chromium (Cr)** | ~14.5 | Oxidation resistance. | | **Cobalt (Co)** | ~13.5 | Solid solution strengthener. | | **Molybdenum (Mo)** | ~3.75 | Solid solution strengthener. | | **Aluminum (Al)** | ~5.0 | Forms the primary strengthening γ' phase (Ni₃Al). | | **Titanium (Ti)** | ~4.0 | Forms the primary strengthening γ' phase (Ni₃Ti). | | **Carbon (C)** | ~0.15 | Carbide formation for grain boundary strength. | | **Boron (B)** | ~0.015 | Grain boundary strengthener. | #### **Physical & Mechanical Properties (Typical)** * **Density:** 7.95 g/cm³ * **Melting Range:** ~1280 - 1340 °C * **Room Temperature Tensile Strength (Aged):** UTS > 1100 MPa, YS > 760 MPa. * **Key Feature:** Outstanding long-term creep and rupture strength at temperatures up to 950°C. #### **Product Applications** * Turbine blades (both aircraft and industrial gas turbines) * Nozzle guide vanes * Other high-stress, high-temperature static and rotating parts #### **International Standards** * **AMS:** 5700 (Bars, Forgings, & Rings) * **ISO:** 9722 (Wrought Nickel-Based Alloy) * **BS:** HR 501 (British Aerospace Standard) * **Proprietary:** Rolls-Royce RPS 707, etc. --- ### **3. ATG W3** #### **Overview** **ATG W3** is a proprietary specification, not a base alloy name. The "ATG" prefix strongly suggests it is a material specification from **Safran Aircraft Engines** (formerly Snecma). "W3" designates a specific grade or version. It almost certainly refers to a high-performance nickel-based superalloy, likely a variant or a specific processing standard for an existing alloy like **Udimet 720** or a similar high-strength forging material. * **Interpretation:** ATG W3 defines not just the chemical composition but also the precise manufacturing route, heat treatment, non-destructive testing (NDT) requirements, and mechanical property limits mandated by Safran for a specific component, typically a **critical turbine disk**. #### **Typical Characteristics (Inferred for a Disk Alloy like U720)** * **Alloy Base:** Likely a Ni-Cr-Co-Mo-Ti-Al superalloy. * **Key Property:** Ultra-high tensile strength and excellent low-cycle fatigue (LCF) resistance at intermediate temperatures (500-750°C), which is critical for turbine disks. * **Form:** Supplied as precision forgings or billets. #### **Chemical Composition (Representative - Based on Common Disk Alloys)** This is an example and *must be verified against the actual specification*. | Element | Representative % | | :--- | :--- | | **Ni** | Balance | | **Cr** | ~16.0 | | **Co** | ~14.7 | | **Mo** | ~3.0 | | **W** | ~1.25 | | **Ti** | ~5.0 | | **Al** | ~2.5 | | **C** | ~0.025 | | **B** | ~0.025 | | **Zr** | ~0.035 | #### **Product Applications** * Primarily used for **High-Pressure Turbine (HPT) Disks / Discs** * **Compressor Disks** in the highest-stress stages * **Shafts** and other critical rotating components in Safran engines (e.g., CFM56, LEAP, etc.) #### **Standards & Specifications** * **Primary Standard:** **Safran ATG W3** specification. This is the controlling document and overrides all other standards. * **Potential Cross-References:** May be equivalent or similar to AMS standards for alloys like Udimet 720 (e.g., AMS 4082, AMS 4083). However, for any component, the ATG W3 specification is absolute. --- ### **Summary Comparison** | Feature | Udimet 700 | Nimonic 115 | ATG W3 (Inferred) | | :--- | :--- | :--- | :--- | | **Primary Strength** | High Tensile & Creep | Superior Creep-Rupture | Ultra-High Tensile & LCF Fatigue | | **Typical Use** | Blades, Disks, Vanes | Turbine Blades, Vanes | Turbine Disks (Rotors) | | **Temp Focus** | Very High (870-980°C) | High (850-950°C) | Intermediate-High (500-750°C) | | **Defining Standard** | AMS, UNS N07700 | AMS, BS HR 501 | **Safran ATG W3 Proprietary Spec** | **Disclaimer:** The information provided is for technical reference and comparison purposes. Properties are typical and can vary with product form, heat treatment, and manufacturing route. **ATG W3 is a proprietary specification, and its exact requirements are defined solely by Safran Aircraft Engines.** For design and procurement, the official, latest issue of the relevant material specification (AMS, ATG, etc.) must be consulted. Udimet and Nimonic are registered trademarks of their respective owners.

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