Haynes 282

metal

nickel superalloy — γ' precipitation-hardened

Alloy 282H282UNS N07208Haynes® 282

Density

8.33 g/cm³

YS (LPBF as-built (XY))

780–1000 MPa

UTS (LPBF as-built (XY))

950–1180 MPa

Elongation (LPBF as-built (XY))

10.0–24.0 %

Thermal conductivity

10.6 W/m·K

Composition — UNS N07208 / Haynes International specification

Element	Min %	Max %	Notes
Ni	—	—	balance — Ni base provides γ matrix stability to ~1200°C
Co	8.00	12.000	~10% Co; γ-matrix solid-solution strengthening; raises γ-solvus temperature
Cr	18.00	22.000	~20% Cr; Cr₂O₃ scale for oxidation resistance to 980°C
Mo	7.00	9.000	~8% Mo; solid-solution strengthening; creep resistance; grain boundary stabilisation
Al	1.30	1.700	~1.5% Al; primary γ'-former (Ni₃Al); moderate Al content reduces cracking risk vs high-Al alloys

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Mechanical & thermal properties — 3 conditions

Property	LPBF as-built (XY)	LPBF full STA (XY) — primary service condition	DED-Laser STA (XY)
Elastic modulus	—	200–220 GPa	—
Yield strength (0.2%)	780–1000 MPa	760–850 MPa	740–830 MPa
Ultimate tensile strength	950–1180 MPa	1080–1200 MPa	1040–1150 MPa
Elongation at break	10.0–24.0 %	20.0–35.0 %	18.0–32.0 %
Hardness (HV)	—	330–390 HV10	—
Fatigue strength	—	520–680 MPa	—
Density	8.33 g/cm³	—	—
Thermal conductivity	10.6 W/m·K	—	—
Max service temperature	—	870–930 °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 precision: anneal at 1080°C/2h (±10°C) in argon or vacuum. First age 1010°C/2h (±10°C) — this step precipitates coarse γ' for creep resistance. Second age 788°C/8h (±10°C) — fine γ' for room-temperature strength. Each stage requires calibrated furnace; monitor with thermocouples at part surface.
Stress relief before STA: LPBF residual stress in Haynes 282 is similar in magnitude to IN718. Consider a pre-anneal stress relief (900°C/1h) before removing from build plate, then proceed to full STA.
HIP consideration: HIP (1100°C/100–150 MPa/3h) before STA closes porosity and improves fatigue life. Required for flight-critical rotating applications. Check that HIP temperature does not coarsen γ' excessively.
Creep design: Haynes International publishes comprehensive Larson-Miller creep rupture curves for wrought Haynes 282. Use these as a conservative baseline for AM design until AM-specific creep test data is available.
IN718 comparison: choose Haynes 282 when service temperature exceeds 650–700°C sustained. Below 650°C, IN718 is preferred due to higher room-temperature UTS, better AM data availability, and lower cost.
DED repair applications: Haynes 282 can be deposited on wrought Haynes 282 or Waspaloy substrates by DED. Pre-heat substrate to 150–200°C to prevent thermal shock cracking. Full STA of the entire component after DED repair.
Surface integrity: as-built Ra 8–15 µm (LPBF). For hot-section components with cooling air channels, electropolishing or abrasive flow machining (AFM) may be needed to reduce surface stress concentrations.

Advantages

Sustained service temperature 900°C — 250°C higher than IN718's 650°C limit
Excellent ductility (26% elongation STA) for a high-strength γ'-strengthened alloy — better fabricability than CM247LC or IN939
Lower hot-cracking susceptibility than Waspaloy during welding/DED due to lower Al+Ti/Mo ratio
Good oxidation resistance to 1000°C in air and combustion atmospheres
Long-term microstructural stability — γ' coarsening rate is low above 760°C, maintaining creep life
Established aeroengine heritage: GE, Siemens, Rolls-Royce have used Haynes 282 in development programmes

Limitations

Full STA cycle is complex (three stages) and must be precisely controlled — temperature and time deviations affect γ' morphology and creep life
As-built LPBF properties are NOT suitable for service — full STA is non-negotiable
Powder cost is 3–6× higher than IN718; powder availability from Haynes International and third-party suppliers is limited
AM-specific creep and fatigue design databases are sparse — must generate test data for each application
Higher density (8.33 g/cm³) and lower strength than some competing Ni alloys — not optimal where weight is critical
No published AM-specific material standard — qualification must use OEM-internal or Haynes International specifications
Machining is difficult (high Co, Cr, Mo) — plan for premium machining costs and specialised tooling

Typical applications

Turbine combustion chamber liners and flame tubes (900°C sustained)Turbine transition ducts and exhaust casingsIndustrial gas turbine hot-section structural componentsTurbine vane carriers and ring segmentsPower generation steam turbine high-temperature fastenersChemical processing reactor internals at >700°CAerospace engine nacelle structural parts requiring creep resistanceRepair of wrought/cast Haynes 282 aeroengine components by DED

Haynes 282

Composition — UNS N07208 / Haynes International specification

Mechanical & thermal properties — 3 conditions

Engineering considerations

Advantages

Limitations

Typical applications

Industries

Compatible AM processes (2)

Other metal materials

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