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GH2150
GH2150 is a Fe-Ni-Cr base precipitation hardening deformation superalloy with service temperature below 750 ℃. Chromium, tungsten and molybdenum are added to the alloy for solid solution strengthening, titanium, aluminum and niobium are added to form aging strengthening phase, and trace boron, zirconium and cerium are added to purify and strengthen the grain boundary. The alloy has high strength, good plasticity, low expansion coefficient and stable structure after long-term use; The alloy has good hot working plasticity and satisfactory welding, cold forming and cutting properties. It is applicable to the manufacture of jet engine plate welding load-bearing structural parts working under 700 ℃, and gas turbine rotor and compressor blade working under 600 ℃ for a long time. The superalloy has been used to make high-temperature components such as the outer jacket of the combustion chamber and the mounting edge of the aviation engine, and the batch production and use conditions are good. Similar alloys have been used in foreign countries for combustion chamber jackets of jet engines and turbine blades and other zero treatment parts used below 600 ℃, and have been tested for long-term use.
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product details
|
Brand |
GH2150 |
|
Similar brands |
GH136 |
| Technicalstandard |
GB/T 14992-2005《Classification and designation of superalloy and intermetallic compound high-temperature materials》 |
|
Classification |
Special alloy steel |
| Performance |
Corrosion resistance Weldability |
| Label | Age-hardening iron-base alloy |
|
Explain |
GH2150 is a Fe-Ni-Cr base precipitation hardening deformation superalloy with service temperature below 750 ℃. Chromium, tungsten and molybdenum are added to the alloy for solid solution strengthening, and boron, zirconium and cerium are added to purify and strengthen the grain boundary. The alloy has high strength, good plasticity, low expansion coefficient and stable structure after long-term use; The alloy has good hot working plasticity and satisfactory welding, cold forming and cutting properties. It is applicable to the manufacture of jet engine plate welding load-bearing structural parts working under 700 ℃, and gas turbine rotor and compressor blade working under 600 ℃ for a long time. GH2150 superalloy has been used to make high-temperature components such as the outer jacket of the combustion chamber and the mounting edge of the aviation engine, and the batch production and use conditions are good. Similar alloys have been used in foreign countries for combustion chamber jackets of jet engines and turbine blades and other zero treatment parts used below 600 ℃, and have been tested for long-term use. |
|
Density |
8.26g/cm3 |
Chemical composition:%
| Element |
Fe |
C |
Si |
Mn |
P |
S |
Cr |
Ni |
Cu |
B |
Mo |
Ti |
W |
Nb |
|
Min. |
Allowance |
- |
- |
- |
- |
- |
14 |
45 |
- |
- |
4.5 |
1.8 |
2.5 |
0.9 |
|
Max. |
0.08 |
0.4 |
0.4 |
0.02 |
0.015 |
16 |
50 |
0.07 |
0.01 |
6 |
2.4 |
3.5 |
1.4 |
| Element |
Fe |
Zr |
Al |
Ce |
|
Min. |
Allowance |
- |
0.8 |
- |
|
Max. |
0.05 |
1.3 |
0.02 |
Note: The above information is for reference only. Some elements in different standards and specifications may be different.
The information of the above materials is rough description, and any deviation may be used for reference only
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