Hastelloy

GH3039

GH3039 is a single-phase austenitic solid solution strengthened alloy with moderate thermal strength and good thermal fatigue properties below 800°C, and good oxidation resistance below 1000°C. The structure is stable after long-term use, and it also has good cold formability and welding performance. Suitable for long-term use of aircraft engine combustion chamber and afterburner components below 850°C. The alloy can be used to produce sheets, rods, wires, tubes and forgings.


Product Description:

GH3039 is a single-phase austenitic solid solution strengthened alloy with moderate thermal strength and good thermal fatigue properties below 800°C, and good oxidation resistance below 1000°C. The structure is stable after long-term use, and it also has good cold formability and welding performance. Suitable for long-term use of aircraft engine combustion chamber and afterburner components below 850°C. The alloy can be used to produce sheets, rods, wires, tubes and forgings.

 

Physical properties:

Density: 8.3g/cm³

Melting point: 900-1170℃

 

Extreme chemical composition:

Nickel: balance

Chromium: 19-22

Iron: 3.0max

Molybdenum: 1.8-2.3

Carbon: 0.08max

Niobium: 0.9-1.3

Aluminum: 0.35-0.75

Manganese: 0.4max

Sulfur: 0.012max

Silicon: 0.8max

Titanium: 0.35-0.75

Phosphorus: 0.02max

 

Minimum mechanical properties of alloys at room temperature

GH3039

Type/mm

tensile strength

Elongation

Plate

735

40

Rod

735

40

cold rolled strip


735

40

δ≤0.25

660

实测

aviation pipe


685

40

OD<30WT>3

635

30

General tube


635

35

 

 

 

 

 

 

 

 

 

 

characteristic:

GH3039 is a single-phase austenitic solid solution strengthened alloy. It has medium thermal strength and good thermal fatigue properties below 800°C, and has good oxidation resistance below 1000°C. The structure is stable after long-term use, and it also has good cold formability and welding performance.

 

Application areas:

Suitable for long-term use of aviation engine combustion chamber and afterburner parts below 850 degrees Celsius

Structural parts of gas turbine combustion chamber

 

form:

Bars, wires, strips, plates, forgings, rings, pipes, etc.


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