Used for gas turbine structural components, such as turbine section frames. The alloy is useful where oxidation resistance and high temperature strength are of major importance.
| Elements | Min.（≥） | Max.（≤） | Similar | Remarks |
|---|---|---|---|---|
| C | - | 0.08 | ||
| Si | - | 0.07 | ||
| Mn | - | 1.00 | ||
| Cr | 14.00 | 17.00 | ||
| Ni | - | Balance | ||
| Cu | - | 0.5 | ||
| Fe | 5.00 | 9.00 | ||
| P | - | - | ||
| S | - | 0.01 | ||
| Ti | 2 | 2.75 | ||
| Al | 0.40 | 1.00 |
Physical Data : [top]
| Proof strength Rp0.2 (MPa) |
Tensile strength Rm (MPa) |
Impact energy KV (J) |
Elongation at fracture A (%) |
Reduction in cross section on fracture Z (%) |
As-Heat-Treated Condition | Brinell hardness (HBW) |
|---|---|---|---|---|---|---|
| 271 (≥) | 948 (≥) | 11 | 33 | 24 | Solution and Aging, Annealing, Ausaging, Q+T,etc | 223 |
| Property | Density kg/dm3 |
Temperature T °C/F |
Specific heat J / kgK |
Thermal conductivity W/mK |
Electric resistance µΩ·cm |
Modulus of elasticity kN/mm2 |
Expansion rate |
|---|---|---|---|---|---|---|---|
| 112 (≥) | 332 (≥) | 31 | 41 | 41 | Solution and Aging, Annealing, Ausaging, Q+T,etc | 124 | |
| Temp. °C/°F |
Creep strain limit (10000h) (Rp1,0) N/mm2 |
Creep rupture strength (10000h) (Rp1,0) N/mm2 |
|||||
| 121 | 235 | 912 |
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