Ti-6Al-2Sn-4Zr-2Mo
Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium alloy developed for elevated temperature performance, offering excellent creep resistance, oxidation stability, and fatigue strength up to 550°C. It is primarily used in aerospace and jet engine applications that demand long-term structural integrity under high thermal stress.
Titanium alloy 3D printing enables the production of lightweight, complex Ti-6-2-4-2 components such as turbine casings, engine mounts, and structural airframe parts. Additive manufacturing reduces material waste and allows high-precision fabrication of mission-critical aerospace hardware.
Ti-6Al-2Sn-4Zr-2Mo Similar Grades Table
Country/Region | Standard | Grade or Designation |
|---|---|---|
USA | UNS | R54620 |
USA | AMS | AMS 4919 |
China | GB | TA19 |
Russia | GOST | VT22 |
Ti-6Al-2Sn-4Zr-2Mo Comprehensive Properties Table
Category | Property | Value |
|---|---|---|
Physical Properties | Density | 4.54 g/cm³ |
Melting Range | 1620–1670°C | |
Thermal Conductivity (20°C) | 6.2 W/(m·K) | |
Thermal Expansion (20–500°C) | 8.5 µm/(m·K) | |
Chemical Composition (%) | Titanium (Ti) | Balance |
Aluminum (Al) | 5.5–6.5 | |
Tin (Sn) | 1.8–2.2 | |
Zirconium (Zr) | 3.8–4.2 | |
Molybdenum (Mo) | 1.8–2.2 | |
Mechanical Properties | Tensile Strength | ≥1000 MPa |
Yield Strength (0.2%) | ≥900 MPa | |
Elongation at Break | ≥10% | |
Modulus of Elasticity | 115 GPa | |
Hardness (HRC) | 32–38 |
3D Printing Technology of Ti-6Al-2Sn-4Zr-2Mo
This alloy is compatible with Selective Laser Melting (SLM), Direct Metal Laser Sintering (DMLS), and Electron Beam Melting (EBM). These processes produce high-performance aerospace components with excellent heat resistance and fatigue performance.
Applicable Process Table
Technology | Precision | Surface Quality | Mechanical Properties | Application Suitability |
|---|---|---|---|---|
SLM | ±0.05–0.2 mm | Excellent | Excellent | Turbine Components, Airframes |
DMLS | ±0.05–0.2 mm | Very Good | Excellent | Jet Engine Casings, Mounts |
EBM | ±0.1–0.3 mm | Good | Very Good | Large Structural Aerospace Parts |
Ti-6Al-2Sn-4Zr-2Mo 3D Printing Process Selection Principles
When tight tolerances (±0.05–0.2 mm) and smooth surfaces (Ra 5–10 µm) are needed, SLM is ideal for printing high-stress components like engine supports and thermal shields.
DMLS is suitable for medium-sized, high-performance aerospace parts requiring precision and repeatability, especially in thermally loaded environments.
For large-scale, thick-walled parts where speed and heat resistance matter, EBM offers good dimensional control (±0.1–0.3 mm) with reliable structural performance in Ti-6-2-4-2.
Ti-6Al-2Sn-4Zr-2Mo 3D Printing Key Challenges and Solutions
Residual stress due to steep thermal gradients is a key issue. Use of optimized support structures and HIP at 900–940°C and 100–150 MPa improves mechanical integrity and fatigue resistance.
Porosity and microcracks can be minimized with optimized parameters (laser power: 250–400 W; scan speed: 600–900 mm/s), achieving >99.8% part density.
Surface roughness (Ra 8–15 µm) can reduce fatigue strength. Use CNC machining and electropolishing to achieve Ra 0.4–1.0 µm.
Strict powder handling protocols are required—oxygen levels <200 ppm, humidity <5% RH—to avoid embrittlement and maintain alloy performance.
Industry Application Scenarios and Cases
Ti-6-2-4-2 is widely used in:
Aerospace: Jet engine casings, turbine parts, airframe structures.
Power Generation: High-temperature compressor housings and blade platforms.
Defense: Missile frames, heat-resistant components.
A recent aerospace case used SLM to produce a turbine casing in Ti-6-2-4-2, reducing weight by 18% and improving high-temperature fatigue life by 27%, significantly enhancing overall engine efficiency.
FAQs
What are the benefits of 3D printing Ti-6Al-2Sn-4Zr-2Mo for aerospace applications?
Which additive manufacturing methods are best suited for this titanium alloy?
How does Ti-6-2-4-2 compare to Ti-6Al-4V in high-temperature performance?
What are common challenges in printing Ti-6Al-2Sn-4Zr-2Mo, and how are they solved?
What post-processing steps are needed to optimize Ti-6-2-4-2 part performance?
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