15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES

15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES Product Information -:- For detailed product information, please contact sales. -: 15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES Synonyms -:- For detailed product information, please contact sales. -:

15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES Product Information -:- For detailed product information, please contact sales. -: # **Product Introduction: 15Cr-28Co-4Mo-2.5Ti-3Al Nickel-Based Superalloy Bar for Gas Turbine Blades** ## **1. Overview** **15Cr-28Co-4Mo-2.5Ti-3Al** is a **γ' precipitation-strengthened, wrought nickel-based superalloy** specifically engineered for **high-pressure turbine blades and critical rotating components** in advanced gas turbine engines. Characterized by its **exceptionally high cobalt content (28%)** and balanced strengthening additions, this alloy is designed to deliver **outstanding high-temperature creep resistance, excellent fatigue strength, and superior microstructural stability** in the **750-950°C (1382-1742°F) service range**. The alloy's composition represents an advanced evolution of conventional turbine blade materials, optimized for applications where thermal and mechanical stresses approach the limits of metallic material capabilities. Its bar product form enables the manufacture of both solid and internally cooled blade designs through advanced machining and forging processes. ## **2. International Standards & Specifications** This specialized superalloy is typically governed by proprietary specifications from major aerospace manufacturers rather than general commercial standards. * **Primary Aerospace Specifications:** * **OEM Proprietary Standards:** Material specifications from **General Electric (GE)**, **Pratt & Whitney (P&W)**, **Rolls-Royce**, or **Safran** (e.g., designations like GTD-XXX, PWA 12XX, RR2000-series, or equivalent proprietary grades). * **AMS 5708 / AMS 5832:** Aerospace Material Specifications for nickel alloy bars, forgings, and rings; while not exact matches, they represent the quality and processing standards required. * **International Equivalents & Related Alloys:** * **Russian Equivalent:** **ЭП742 (EP742)** or similar high-cobalt nickel alloys developed for turbine applications. * **European Designation:** May correspond to specialized grades within proprietary European aerospace programs. * **Japanese Equivalent:** Advanced alloys developed by **IHI Corporation** or **Mitsubishi Heavy Industries** for gas turbine applications. * **Related Commercial Alloys:** Shares design principles with **Udimet 720**, **René 65**, **IN-100** (with higher Co), and **TMW-4M3**, but with distinct Cr/Co balance. ## **3. Chemical Composition (Weight %, Typical)** | Element | Typical Range (%) | Role & Benefit | |---------|-------------------|----------------| | **Nickel (Ni)** | Balance (~48-52%) | Austenitic (γ) matrix; provides fundamental corrosion resistance and serves as base for γ' precipitation. | | **Chromium (Cr)** | 14.5 – 15.5 | Provides **oxidation and hot corrosion resistance** via formation of protective Cr₂O₃ scale. | | **Cobalt (Co)** | 27.5 – 28.5 | **Critical strengthening element.** Enhances high-temperature strength, reduces stacking fault energy, improves γ' stability, and increases solvus temperature. | | **Molybdenum (Mo)** | 3.8 – 4.2 | **Powerful solid-solution strengthener.** Increases high-temperature strength and creep resistance, reduces diffusion rates. | | **Aluminum (Al)** | 2.8 – 3.2 | **Primary γ' former (Ni₃Al).** Key precipitation strengthening element; contributes to oxidation resistance via Al₂O₃ scale. | | **Titanium (Ti)** | 2.3 – 2.7 | **γ' former (Ni₃Ti).** Synergizes with Al to increase γ' volume fraction and anti-phase boundary (APB) energy. | | **Tungsten (W)** | (May be present, 2-4%) | Additional solid-solution strengthening; improves high-temperature capability. | | **Tantalum (Ta)** | (May be present, 1-3%) | Refractory element that partitions to γ', enhancing its high-temperature strength and stability. | | **Niobium (Nb)** | (May be present, 0.5-1.5%) | γ' former and carbide stabilizer; improves intermediate temperature strength. | | **Carbon (C)** | 0.03 – 0.08 | Forms primary MC carbides for grain boundary pinning and strengthening. | | **Boron (B)** | 0.010 – 0.020 | **Grain boundary strengthener.** Segregates to boundaries, improving creep rupture life and ductility. | | **Zirconium (Zr)** | 0.03 – 0.08 | Trace addition to enhance grain boundary cohesion and creep properties. | ## **4. Typical Physical & Mechanical Properties (Heat Treated Condition)** * **Heat Treatment:** * **Solution Treatment:** 1100-1150°C (2012-2102°F) followed by rapid cooling. * **Aging Treatment:** Multi-stage aging (e.g., 850°C + 750°C) to optimize γ' precipitation distribution. * **Room Temperature Properties:** * **Tensile Strength:** 1300 – 1500 MPa (188,500 – 217,500 psi) * **Yield Strength (0.2% Offset):** 1100 – 1300 MPa (159,500 – 188,500 psi) * **Elongation:** 10 – 18% * **Reduction of Area:** 15 – 25% * **Hardness:** 38 – 44 HRC * **Elevated Temperature Performance (900°C / 1652°F):** * **Stress Rupture Life (240 MPa / 35 ksi):** > 200 hours * **Creep Strength (0.2% in 1000h):** > 150 MPa (21,750 psi) * **Low-Cycle Fatigue Life (Δε=0.8%, 900°C):** > 5,000 cycles * **Physical Properties:** * **Density:** 8.25 – 8.45 g/cm³ * **Melting Range:** 1340 – 1390°C (2444 – 2534°F) * **Modulus of Elasticity:** 205 GPa (29.7 × 10⁶ psi) at 20°C; ~160 GPa at 900°C * **Thermal Conductivity:** 16 – 19 W/m·K (at 800°C) * **Coefficient of Thermal Expansion:** 14.0 – 15.0 × 10⁻⁶/°C (20–800°C) ## **5. Product Application** * **Aerospace Gas Turbines:** * **High-Pressure Turbine (HPT) Blades** in commercial and military jet engines * **Turbine Disks and Blisks** (integrally bladed disks) for advanced engine designs * **Compressor Blades** in later, high-temperature stages * **Industrial & Power Generation Gas Turbines:** * **First and Second Stage Turbine Blades** in heavy-duty industrial turbines * **Turbine Wheels and Rotors** for power generation applications * **Aero-derivative Turbine Components** * **Marine Propulsion:** * **Gas Turbine Blades** for naval ship propulsion systems * **Specialized Applications:** * **Rocket Engine Turbopump Components** * **High-Temperature Fasteners and Bolting** ## **6. Key Features & Advantages** * **Exceptional High-Temperature Strength:** High cobalt content significantly enhances creep resistance and microstructural stability at elevated temperatures. * **Superior Fatigue Resistance:** Excellent resistance to both high-cycle and low-cycle fatigue, critical for rotating components. * **Optimized γ' Precipitation:** Balanced Al+Ti content provides high γ' volume fraction (~40-50%) with good thermal stability. * **Good Oxidation & Corrosion Resistance:** 15% Cr content provides adequate protection in most turbine environments. * **Excellent Forgeability & Machinability:** As a wrought alloy, it offers better hot workability than cast equivalents, allowing for more complex component designs. * **Isotropic Properties:** Bar product form provides consistent properties in all directions, beneficial for complex loading conditions. * **Repairability:** Components can often be repaired via specialized welding and recoating processes. ## **7. Manufacturing & Processing Considerations** * **Melting Practice:** Requires **Vacuum Induction Melting (VIM)** followed by **Vacuum Arc Remelting (VAR)** or **Electroslag Remelting (ESR)** for optimal cleanliness and homogeneity. * **Hot Working:** Forged in the temperature range of 1050-1150°C; requires precise temperature control due to narrow processing window. * **Heat Treatment:** Critical for developing optimal mechanical properties; requires tightly controlled furnace atmospheres and cooling rates. * **Machining:** Challenging in aged condition; typically performed in solution-treated state followed by final aging. * **Surface Treatment:** Typically coated with **MCrAlY bond coats** and **thermal barrier coatings (TBCs)** for maximum temperature capability. * **Quality Control:** Requires extensive non-destructive testing (NDT) including ultrasonic, eddy current, and fluorescent penetrant inspection. ## **8. Design & Performance Considerations** * **Temperature Capability:** Maximum continuous service temperature of ~950°C (1742°F) for coated components. * **Creep Performance:** Exceptional long-term creep resistance makes it suitable for components requiring extended service life. * **Thermal Expansion:** Similar to other nickel superalloys; requires consideration in assembly with dissimilar materials. * **Cost Factor:** High cobalt content makes this an expensive material, typically reserved for critical applications. * **Supply Chain:** Limited to specialized mills with appropriate melting and processing capabilities. **Summary:** The 15Cr-28Co-4Mo-2.5Ti-3Al nickel-based superalloy bar represents an advanced material solution for gas turbine blades requiring exceptional high-temperature performance. Its high cobalt content provides unique advantages in creep resistance and microstructural stability, while maintaining adequate environmental resistance. This alloy enables turbine designers to push the boundaries of engine efficiency and performance through higher operating temperatures and stresses, contributing to the development of next-generation propulsion systems with improved fuel efficiency and reduced emissions. -:- For detailed product information, please contact sales. -: 15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES Specification Dimensions Size： Diameter 20-1000 mm Length <7023 mm Size:We can customized as required Standard： Per your request or drawing We can customized as required Properties（Theoretical） Chemical Composition -:- For detailed product information, please contact sales. -: 15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES Properties -:- For detailed product information, please contact sales. -:

Applications of 15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES -:- For detailed product information, please contact sales. -: Chemical Identifiers 15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES -:- For detailed product information, please contact sales. -:

Packing of 15Cr-28Co-4Mo-2.5Ti-3Al NICKEL BASED SUPERALLOY BARS FOR GAS TURBINE BLADES -:- For detailed product information, please contact sales. -: Standard Packing: -:- For detailed product information, please contact sales. -: 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 3494 gallon liquid totes Special package is available on request. E FORUs’ is carefully handled to minimize damage during storage and transportation and to preserve the quality of our products in their original condition