Haynes 282
metalnickel superalloy — γ' precipitation-hardened
Alloy 282H282UNS N07208Haynes® 282
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 |
| Ti | 1.90 | 2.400 | ~2.1% Ti; γ'-former (Ni₃Ti component); higher Ti than IN718 increases γ' volume fraction and creep resistance |
| Fe | — | 1.500 | |
| C | 0.04 | 0.080 | Controlled carbide former (MC, M₂₃C₆) — carbides pin grain boundaries for creep |
| B | 0.00 | 0.010 | Grain boundary strengthening — critical for creep rupture life |
| Mn | — | 0.300 | |
| Si | — | 0.150 | |
| P | — | 0.015 | |
| S | — | 0.015 | |
| Cu | — | 0.100 |
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
Industries
aerospaceenergyindustrial
Compatible AM processes (2)
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Related calculators
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Last reviewed: 2026-05-13 · v1 · Sources: haynes-282-2023, smith-2019-h282-lpbf, tong-2021-h282-creep
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