Specification for aircraft material. 24/17 chromium-nickel heat-resisting steel (titanium stabilized) (35 tonf/sq in: limiting ruling section 6 in)
| Elements | Min.（≥） | Max.（≤） | Similar | Remarks |
|---|---|---|---|---|
| C | - | 0.15 | ||
| Si | 0.20 | 1.00 | ||
| Mn | 0.50 | 2.00 | ||
| P | - | 0.035 | ||
| S | - | 0.025 | ||
| Cr | 23.00 | 26.00 | ||
| Ni | 16.00 | 19.00 | ||
| Mo | - | - | ||
| Ti | - | 4×C |
Specification for aircraft material. 24/17 chromium-nickel heat-resisting steel (titanium stabilized) (35 tonf/sq in: limiting ruling section 6 in)
| 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) |
|---|---|---|---|---|---|---|
| 559 (≥) | 659 (≥) | 21 | 41 | 22 | Solution and Aging, Annealing, Ausaging, Q+T,etc | 344 |
| 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 |
|---|---|---|---|---|---|---|---|
| 811 (≥) | 586 (≥) | 21 | 21 | 33 | Solution and Aging, Annealing, Ausaging, Q+T,etc | 221 | |
| Temp. °C/°F |
Creep strain limit (10000h) (Rp1,0) N/mm2 |
Creep rupture strength (10000h) (Rp1,0) N/mm2 |
|||||
| 482 | 894 | 823 |
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