Superalloy GH3044: Solid-Solution Strengthened Nickel Alloy for Aero-Engine Hot Sections
Superalloy GH3044: Solid-Solution Strengthened Nickel Alloy for Aero-Engine Hot Sections
1. Introduction to GH3044 Alloy GH3044 is a single‑phase austenitic solid‑solution strengthened nickel‑based alloy engineered for reliable long‑term service in high‑temperature environments. The material delivers moderate thermal strength and excellent thermal‑fatigue resistance below 800 °C, combined with outstanding oxidation resistance up to 1000 °C. GH3044 maintains exceptional structural stability over time, while its good cold formability and excellent welding performance make it a versatile choice for demanding engineering applications. 2. Key Properties of GH3044 Nickel Alloy Solid‑solution strengthened, single‑phase austenitic structure Stable mechanical properties during long‑term service Excellent oxidation resistance up to 1000 °C Superior thermal‑fatigue resistance below 800 °C Outstanding cold forming and welding performance 3. Available Product Forms We supply GH3044 alloy in a wide range of forms to meet diverse industrial…
GH3044 is a single‑phase austenitic solid‑solution strengthened nickel‑based alloy engineered for reliable long‑term service in high‑temperature environments. The material delivers moderate thermal strength and excellent thermal‑fatigue resistance below 800 °C, combined with outstanding oxidation resistance up to 1000 °C. GH3044 maintains exceptional structural stability over time, while its good cold formability and excellent welding performance make it a versatile choice for demanding engineering applications.
GH3044 is widely used in aerospace and high‑temperature engineering, particularly for components that must operate reliably at temperatures up to 850 °C:
Aero‑engine combustion chambers
Afterburner parts
Other high‑temperature structural components
5. Chemical Composition
Element
Symbol
Requirement (wt.%)
Nickel
Ni
Balance
Chromium
Cr
23.5 – 26.5
Tungsten
W
13.0 – 16.0
Iron
Fe
≤ 4.0
Molybdenum
Mo
≤ 1.50
Titanium
Ti
0.30 – 0.70
Aluminum
Al
≤ 0.50
Carbon
C
≤ 0.10
Silicon
Si
≤ 0.80
Manganese
Mn
≤ 0.50
Copper
Cu
≤ 0.25
Phosphorus
P
≤ 0.013
Sulfur
S
≤ 0.013
6. Physical Properties
Constant
Metric Value
Density (g/cm³)
8.89
Melting Range (°C)
1352 – 1375
Thermal Conductivity @ 20 °C (W/m·K)
11.7
Specific Heat (J/kg·K)
435
7. Room Temperature Mechanical Properties (Typical)
Property
Value
Tensile Strength, σb (MPa)
≥ 700
Yield Strength, σ0.2 (MPa)
≥ 300
Elongation, δ5 (%)
≥ 35
Hardness (HBW)
≤ 220
8. Elevated‑Temperature Tensile and Stress‑Rupture Properties
(Values shown are minimum unless otherwise stated)
Product Type
Heat Treatment
RT σb (MPa)
RT δ5 (%)
RT ψ (%)
900 °C σb (MPa)
900 °C δ5 (%)
900 °C ψ (%)
850 °C σ (MPa)
850 °C τ (h)
850 °C δ5 (%)
Cold‑rolled sheet
1120 ~ 1160 °C / AC
735
40
–
195
30
–
–
–
–
Ring blank
1120 ~ 1160 °C / AC
705
40
–
195
30
–
80
Measured
–
Hot‑rolled & forged bar
1120 ~ 1160 °C / AC
685
40
45
195
30
40
70
23
–
Hot‑rolled sheet
1120 ~ 1160 °C / AC
735
40
–
185
30
–
–
–
–
Cold‑rolled strip
1120 ~ 1160 °C / AC
735
40
–
–
–
–
–
–
–
Ring part
1120 ~ 1160 °C / AC or OQ
705
40
–
195
30
–
80
Measured
–
9. Heat Treatment
Process
Temperature
Purpose
Solution Treatment
1150 – 1200 °C
Improve structural uniformity
Rapid Cooling
Water / air cooling
Stabilize austenitic structure
Stress‑Relief Annealing
900 – 1000 °C
Reduce residual stresses
10. Welding Performance
Welding Method
Typical Application
TIG Welding
Pipe and thin‑wall components
MIG Welding
Large structural components
Laser Welding
Precision aerospace parts
11. Melting and Casting
The alloy is produced using electric‑arc furnace, non‑vacuum induction furnace, or vacuum induction furnace followed by electroslag remelting or vacuum arc remelting.
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