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1. Material Overview
GH4141 (GH141 / UNS N07041) is a precipitation-hardening Ni-Cr-Co-Mo superalloy, strengthened by gamma prime (γ’) precipitates and molybdenum solid solution. It offers high tensile strength, excellent creep resistance, and thermal fatigue stability up to 950°C, combined with superior oxidation and hot corrosion resistance. Its creep strength exceeds that of GH4145 and many Inconel‑series alloys, making it a preferred choice for hot‑end components in aero‑engines and industrial gas turbines.
2. GH4141 Chemical Composition (wt%)
All chemical composition data strictly complies with official GB/T standards and UNS N07041 registration specifications. Precise control of aluminum, titanium, molybdenum, and trace boron/zirconium ensures stable precipitation strengthening and effective grain boundary toughening.
| Element | Specification (wt%) | Role & Benefit |
|---|---|---|
| Carbon (C) | 0.06 – 0.12 | Carbide formation, strength |
| Chromium (Cr) | 18.00 – 20.00 | High-temperature oxidation & hot corrosion resistance |
| Cobalt (Co) | 10.00 – 12.00 | High-temperature creep resistance, structural rigidity |
| Molybdenum (Mo) | 9.00 – 10.50 | Solid-solution strengthening, creep resistance |
| Aluminum (Al) | 1.40 – 1.80 | Gamma prime (γ’) former, high-temperature stability |
| Titanium (Ti) | 3.00 – 3.50 | Gamma prime (γ’) former, precipitation hardening |
| Iron (Fe) | 5.00 max | – |
| Boron (B) | 0.003 – 0.010 | Grain boundary strengthening, inhibits sliding |
| Zirconium (Zr) | 0.07 max | Grain boundary toughening |
| Silicon (Si) | 0.50 max | – |
| Manganese (Mn) | 0.50 max | – |
| Phosphorus (P) / Sulfur (S) | 0.015 max each | Strictly controlled impurities |
| Nickel (Ni) | Balance | Matrix element |
Note: Chromium provides high-temperature oxidation and hot corrosion resistance. Cobalt and molybdenum significantly improve creep resistance and structural rigidity. Aluminum and titanium form nano-scale γ’ strengthening phases for mechanical stability. Trace boron and zirconium purify grain boundaries, inhibit high-temperature grain sliding, and effectively extend fatigue service life.
3. Standard Heat Treatment & Mechanical Properties
3.1 Heat Treatment Process
GH4141 achieves optimal comprehensive performance through standardized solution annealing + double aging precipitation hardening:
- Solution Treatment: 1080–1120°C – full solid solution of alloying elements, followed by air cooling.
- Primary Aging: 900–950°C – initiates uniform precipitation.
- Secondary Aging: 800–850°C – precipitates uniform, dense γ’ strengthening phases.
This process eliminates forging residual stresses, stabilizes the grain structure, and maximizes high-temperature strength and thermal fatigue resistance. All production batches include complete heat treatment records and performance test reports.
3.2 Typical Room & High-Temperature Mechanical Properties
(Standard heat-treated condition, GB/T certified typical values)
- Room Temperature Tensile Strength: ≥ 1170 MPa
- Room Temperature Yield Strength (0.2% Offset): ≥ 880 MPa
- Elongation: ≥ 15%
- Hardness: 320 – 380 HB
- Stress-Rupture Strength at 900°C: Excellent creep resistance; stable long-term load-bearing capacity under high-temperature static load.
3.3 Physical & Service Characteristics
- Density: 8.27 g/cm³
- Continuous Service Temperature Range: -196°C to 950°C
- Thermal Properties: Low thermal expansion coefficient, high thermal stability, excellent thermal shock resistance.
- Service Behavior: Maintains stable structural strength and dimensional accuracy under repeated heating and cooling cycles, with strong resistance to high-temperature oxidation, flue gas hot corrosion, and stress fatigue failure.
4. UNS N07041 Core Performance Advantages
4.1 Industry-Leading High-Temperature Creep Resistance
Benefiting from combined molybdenum solid-solution strengthening and a high-density γ’ precipitation phase, GH4141 maintains ultra-high creep rupture strength at 800–950°C, far exceeding conventional GH3044, GH4169, and GH4145 alloys. It withstands long-term constant-load operation in ultra-high-temperature gas environments without structural creep deformation, making it ideal for core hot-end load-bearing components.
4.2 Excellent Thermal Fatigue & Thermal Shock Resistance
Optimized grain boundary toughening through boron and zirconium microalloying effectively inhibits crack initiation and propagation under thermal cycling. The alloy resists thermal fatigue failure caused by frequent temperature fluctuations, adapting reliably to the alternating working conditions of aero-engines and industrial gas turbines.
4.3 Superior High-Temperature Oxidation & Hot Corrosion Resistance
A high chromium content forms a dense, adherent chromium oxide protective film at high temperatures, isolating the base metal from oxygen and corrosive flue gas attack. GH4141 delivers outstanding resistance to high-temperature oxidation, sulfide corrosion, and combustion gas hot corrosion, ensuring long-term, stable service in harsh high-temperature combustion environments.
4.4 Stable Structural Performance & Low Defect Rate
Produced by vacuum induction melting + electroslag remelting (VIM+ESR) double smelting, the alloy features a pure metallurgical structure with uniform grain size and no internal porosity or inclusion defects. It offers consistent mechanical performance from batch to batch and a low high-temperature failure rate, meeting stringent aerospace and energy equipment quality standards.
4.5 Reliable Processability for Precision Manufacturing
After standard heat treatment, GH4141 exhibits a balanced combination of strength and toughness, supporting precision CNC machining, hot forging, rolling, and welding. It can be welded using matched superalloy welding wires with low welding crack sensitivity, making it suitable for manufacturing complex-shaped, high-temperature precision structural parts.
5. Product Range & Specifications
We supply a full range of GB/UNS standard GH4141 superalloy products for high-temperature, high-load industrial equipment, fully integrated with our high-end alloy product system:
- Forged Components & Pipe Fittings: High-temperature forged elbows, tees, reducers, special-shaped pressure forgings, engine structural forgings. Customized high-load hot-end precision forgings available.
- Seamless Pipes & Tubes: High-temperature resistant seamless tubes, OD 16 mm – 630 mm, wall thickness 3 mm – 80 mm. Fixed-length cutting and non-standard customization supported.
- Plates, Sheets & Bar Products: Thick high-temperature plates, thin sheets, round bars, and flat bars for thermal system structural parts and fastener raw materials.
- Custom Ring & Disk Forgings: Turbine ring forgings, disk blanks, and high-temperature equipment supporting structural parts for gas turbine units.
Factory Quality Assurance: VIM+ESR double smelting purity guarantee, full-batch PMI spectral inspection, high-temperature mechanical performance testing, 100% UT/MT non-destructive testing, complete dimensional verification. All products delivered with EN 10204 3.1 mill test certificates.
6. GH141 Main Application Fields
- Aerospace & Aviation Industry: Aero-engine turbine disks, turbine blades, combustion chamber components, high-temperature fasteners, and hot-end structural parts.
- Industrial Gas Turbine & Power Generation: Gas turbine hot-end components, combustion cylinder liners, high-temperature heat exchange pipelines, and power unit thermal structural parts.
- Petrochemical High-Temperature Equipment: High-temperature reaction furnace tubes, cracking furnace components, high-pressure high-temperature process pipeline systems.
- High-End Thermal & Energy Equipment: Ultra-high-temperature thermal system supporting parts, thermal cycling equipment components, and high-load anti-thermal-fatigue structural parts.
- Aerospace & Military Industry: Rocket engine high-temperature components, high-precision thermal fatigue resistant structural forgings.
7. Quality Control & Product Marking
All GH4141 superalloy products follow a unified, full-process quality control workflow consistent with our complete alloy series:
- Raw material smelting purity inspection
- Forging & forming
- Standard solution + aging heat treatment
- Precision machining
- High-temperature mechanical performance testing
- NDT non-destructive flaw detection (UT/MT)
- Dimensional tolerance calibration
- Laser permanent marking
- Vacuum dust-proof & moisture-proof packaging
Standard laser marking includes brand information, grade designation (GH4141/GH141/UNS N07041), execution standard, heat batch number, product specification, and production serial number, ensuring complete traceability for international third-party inspection and high-end engineering procurement acceptance.
8. Future Industry Development Trends
- Upgraded Demand for High-Thrust Aero-Engine Components: As high-thrust aero-engines and heavy-duty gas turbines evolve, GH4141 will progressively replace certain medium-performance superalloys, becoming the mainstream material for 900°C+ hot-end core components.
- Precision Forging & Near-Net-Shape Manufacturing Expansion: Advanced precision forging and additive manufacturing processes reduce material waste and improve component dimensional accuracy, addressing the need for complex, high-precision structural parts in high-end equipment.
- Strict Traceability & High-Purity Melting Standardization: Military and aerospace procurement imposes increasingly higher requirements for alloy purity, trace element control, and batch consistency. Double vacuum melting (VIM+ESR) will become the mandatory production standard for high-grade GH4141 products.
- Expanded Application in New Energy Power Equipment: New energy high-temperature thermal power generation and hydrogen energy high-temperature reaction equipment are driving incremental demand for GH4141 superalloys with high creep strength.
- Digital Simulation for Heat Treatment Process Optimization: Finite element thermal simulation and aging process parameter optimization will further stabilize high-temperature fatigue performance, extend component service life, and reduce overall equipment operation and maintenance costs.
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