Ti-6Al-2Sn-4Zr-2Mo

metal

titanium alloy — near-alpha

Ti-6-2-4-2Ti6242UNS R54620Grade 6 TitaniumAMS 4919 (sheet)ASTM B265 Gr.6

Density

4.55 g/cm³

YS (LPBF as-built (XY))

950–1180 MPa

UTS (LPBF as-built (XY))

1050–1280 MPa

Elongation (LPBF as-built (XY))

2.0–8.0 %

Composition — UNS R54620 / AMS 4919 / ASTM B265 Grade 6

Element	Min %	Max %	Notes
Ti	bal.		balance
Al	5.50	6.500	Alpha stabiliser; solid-solution strengthening
Sn	1.80	2.200	Solid-solution strengthening; negligible effect on transus; improves creep resistance
Zr	3.60	4.400	Solid-solution strengthening; reduces beta fraction; key to elevated-temperature creep resistance
Mo	1.80	2.200	Beta stabiliser (weak); solid-solution strengthening; reduces beta-transus slightly

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Mechanical & thermal properties — 3 conditions

Property	LPBF as-built (XY)	LPBF STA (XY) — primary service condition	LPBF STA (Z)
Elastic modulus	—	108–118 GPa	—
Yield strength (0.2%)	950–1180 MPa	950–1060 MPa	820–950 MPa
Ultimate tensile strength	1050–1280 MPa	1050–1160 MPa	900–1050 MPa
Elongation at break	2.0–8.0 %	8.0–14.0 %	5.0–12.0 %
Hardness (HV)	—	310–370 HV10	—
Fatigue strength	—	480–620 MPa	—
Density	4.55 g/cm³	—	—
Max service temperature	—	450–540 °C	—

Values shown as min–max where a spread is reported, otherwise as typical ± unit. Ranges reflect inter-source variation, not single-sample scatter. All values are for AM-processed specimens unless noted.

Engineering considerations

STA cycle specification: solution treat at 900°C/1h (not above beta transus ~990°C — grain growth risk) + age 565°C/8h. Temperature tolerances ±15°C. Verify with hardness or microstructural checks on coupon specimens.
Residual stress: Ti-6-2-4-2 develops high residual stress in LPBF similar to Ti-6Al-4V. Stress relieve (800°C/2h) before removal from build plate if distortion risk is high, then proceed to full STA.
Creep design: use established wrought Ti-6-2-4-2 Larson-Miller creep data as conservative baseline. AM creep data is not yet published in peer-reviewed literature — generate test data for any creep-critical application.
HIP recommendation: for fatigue-critical or fracture-critical applications, specify HIP (900°C/100 MPa/2h) before STA. Closes gas porosity that would otherwise initiate fatigue cracks. Required by most aerospace primes.
Build orientation for rotating components: align primary load axis in XY plane. After STA, Z-direction properties are acceptable for most applications but design allowables should be based on Z-direction test data.
Powder management: store under argon or vacuum; GRCop-84 oxygen pickup risk applies here too. Verify powder chemistry before reuse — oxygen limits are tighter for near-alpha alloys than alpha-beta.

Advantages

Service temperature 450–500°C vs ~315°C for Ti-6Al-4V — opens mid-temperature aerospace applications
Lower density (4.55 g/cm³) than Ni superalloys (8.2–8.9 g/cm³) — critical weight saving in rotating components
LPBF enables net-shape or near-net-shape complex blades and vanes, reducing machining of this difficult-to-cut alloy
Solid-solution strengthening (Zr, Mo, Sn) is stable — no precipitation dissolution risk during in-service thermal excursions
Good oxidation resistance to 600°C in air (TiO₂ scale formation)
Well-established wrought material heritage in GE90, CF6, and RB211 engine families provides comparative baseline

Limitations

STA post-processing is mandatory — as-built properties are poor (brittle martensite, high residual stress)
Less data available for AM-specific mechanical properties vs Ti-6Al-4V; design databases are sparse
Lower ductility than Ti-6Al-4V STA (10% vs 15% typical elongation) — requires more conservative design allowables
Higher material cost than Ti-6Al-4V powder due to Sn, Zr, Mo additions and smaller production volumes
Near-alpha alloys are more difficult to hot-form than alpha-beta; this affects LPBF support structure removal
No AM-specific material standard (no ASTM F equivalent to F2924 for Ti-6Al-4V)
Fatigue data for LPBF condition is sparse — generate specific test data before creep-critical design

Typical applications

Turbofan engine compressor blades and vanes (intermediate pressure stages)Fan frame and nacelle structural componentsTurbine exhaust case structureAeroengine intermediate compressor discs (creep-critical)Supersonic aircraft structural panels exposed to aerodynamic heatingEngine nacelle and thrust reverser structureHigh-temperature fasteners and brackets in engine hot sections

Ti-6Al-2Sn-4Zr-2Mo

Composition — UNS R54620 / AMS 4919 / ASTM B265 Grade 6

Mechanical & thermal properties — 3 conditions

Engineering considerations

Advantages

Limitations

Typical applications

Industries

Compatible AM processes (2)

Other metal materials

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