Alloy ХН73МБТЮ (ЭИ698)
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Alloy KhN73MBTU (EI698)
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Alloy KhN55VMTFKU (EI929)
Alloy KhN55VMTKU (EI929)
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Alloy KhN53KVMTYUB (EP741P)
Alloy KhN57VKYUTMBL (ZhS6)
Alloy KhN51MTYUKFR (EP220)
Alloy KhN51KVMTYUB (EP741NP)
Alloy KhN50KVMTYUB (BB750)
Alloy KhN50VMTYUB (EP648)
Alloy KhN50VMTKFY (EP57)
Alloy KhN45MVTYUBR (EP718)
Alloy Kh15N60Yu3A (EP548)
Alloy H95S3Yu (EP711)
Alloy H95G (EP18)
Alloy H70M (EP495)
Designation
| Name | The value |
|---|---|
| Designation GOST Cyrillic | ХН73МБТЮ |
| Designation GOST Latin | XH73MBTJu |
| Transliteration | HN73MBTYu |
| The chemical elements | CrNi73CuBeTeAl |
| Name | The value |
|---|---|
| Designation GOST Cyrillic | ЭИ698 |
| Designation GOST Latin | EI698 |
| Transliteration | EhI698 |
| The chemical elements | - |
Description
Alloy ХН73МБТЮ used: for the manufacture of parts for aircraft (gas turbine blades, heat-treated and oblicheny forgings of disks, baffles, labyrinths and socks) with operating temperatures up to +750 °C; mounting and other details, operating at temperatures up to 750−800 °C.
Note
High-temperature Nickel-based alloy.
Standards
| Name | Code | Standards |
|---|---|---|
| Sectional and shaped rolling | В32 | GOST 22411-77, TU 14-1-1973-77, TU 14-1-2792-79 |
| Bulls. Blanks. Slabs | В31 | OST 1 90330-82, TU 14-1-1911-76, TU 14-131-665-86, TU 1-809-694-99, TU 1-809-823-99, TU 1-92-187-92 |
| Metal forming. Forgings | В03 | TU 14-1-1466-75, TU 14-1-1530-75, TU 14-1-285-72, TU 14-1-5329-96 |
Chemical composition
| Standard | C | S | P | Mn | Cr | Si | Ni | Fe | As | Al | B | Ti | Mo | Sn | Sb | Pb | Bi | Nb | Ce |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| TU 14-1-2792-79 | 0.03-0.07 | ≤0.007 | ≤0.015 | ≤0.4 | 13-16 | ≤0.5 | The rest | ≤2 | - | 1.45-1.8 | ≤0.005 | 2.37-2.75 | 2.8-3.2 | - | - | ≤0.001 | - | 1.9-2.2 | ≤0.005 |
| TU 14-1-285-72 | 0.03-0.07 | ≤0.007 | ≤0.015 | ≤0.4 | 13-16 | ≤0.5 | The rest | ≤2 | ≤0.001 | 1.45-1.8 | ≤0.005 | 2.35-2.75 | 2.8-3.2 | ≤0.001 | ≤0.001 | ≤0.001 | ≤0.0001 | 1.9-2.2 | ≤0.005 |
Ni is the basis.
According to TU 14-1-2792-79, the chemical composition is given for the alloy grade KhN73MBTU-VD (EI698-VD). The content of Sb (antimony), Sn (tin), Bi (bismuth), As (arsenic) - no more than 1 point on the scale of spectral analysis. Boron, cerium and other technological additives introduced into the metal by calculation, chemical analysis are not determined. If all the requirements in the finished product are met, deviations from the chemical composition standards are allowed: for carbon ± 0.01%, silicon + 0.1%, niobium + 0.1%, for aluminum -0.05%. The residual content of tungsten is not more than 0.2% is not a rejection sign.
According to TU 14-1-285-72, the chemical composition is given for the alloy grade KhN73MBTU (EI698). Boron, cerium, and other technological additives introduced into the metal by calculation by chemical analysis are not determined. Subject to the requirements of the technical specification, deviations from the chemical composition standards are allowed: by carbon ± 0.010%, silicon + 0.10%, aluminum + 0.10%, titanium + 0.050%, niobium + 0.10%. The content of residual elements is according to GOST 5632.
According to TU 14-1-2792-79, the chemical composition is given for the alloy grade KhN73MBTU-VD (EI698-VD). The content of Sb (antimony), Sn (tin), Bi (bismuth), As (arsenic) - no more than 1 point on the scale of spectral analysis. Boron, cerium and other technological additives introduced into the metal by calculation, chemical analysis are not determined. If all the requirements in the finished product are met, deviations from the chemical composition standards are allowed: for carbon ± 0.01%, silicon + 0.1%, niobium + 0.1%, for aluminum -0.05%. The residual content of tungsten is not more than 0.2% is not a rejection sign.
According to TU 14-1-285-72, the chemical composition is given for the alloy grade KhN73MBTU (EI698). Boron, cerium, and other technological additives introduced into the metal by calculation by chemical analysis are not determined. Subject to the requirements of the technical specification, deviations from the chemical composition standards are allowed: by carbon ± 0.010%, silicon + 0.10%, aluminum + 0.10%, titanium + 0.050%, niobium + 0.10%. The content of residual elements is according to GOST 5632.
Mechanical characteristics
| Section, mm | sT|s0,2, MPa | σB, MPa | d5, % | y, % | kJ/m2, кДж/м2 | Brinell hardness number, MPa |
|---|---|---|---|---|---|---|
| Forgings on the other 14-1-285-72. The longitudinal samples. Hardening in air, 1100-1120 °C (exposure 8 h) + Annealing in air, 990-1010 °C (exposure 4 h) + Ageing at 775±10°C (aging 16 hours), air cooling | ||||||
| ≥706 | ≥1128 | ≥16 | ≥18 | ≥390 | 294-341 | |
| ≥706 | ≥1128 | ≥17 | ≥19 | ≥490 | 294-341 | |
| Forgings on the other 14-1-285-72. The longitudinal samples. Hardening in air, 1100-1120 °C (exposure 8 h) + Annealing in air, 990-1010 °C (exposure 4 h) + Ageing at 775±10°C (aging 16 hours), air cooling + Ageing at 700±10°C (aging 16 hours), air cooling | ||||||
| ≥726 | ≥1157 | ≥14 | ≥16 | ≥390 | 302-363 | |
| The pressed bars. Quenching with 1100-1120 °With, exposure time 8 hours, air cooling, 1000±10 °With exposure 4 hours, air cooling + Ageing at 775±10°C for 16 hours, air cooling | ||||||
| ≥720 | ≥1150 | ≥17 | ≥19 | ≥490 | 294-341 | |
| The pressed bars. Quenching with 1100-1120 °With, exposure time 8 hours, air cooling, 1000±10 °With exposure 4 hours, air cooling. Ageing at 775±10°C for 16 hours, air cooling, aging at 700±10°C for 16 hours, air cooling | ||||||
| ≥740 | ≥1180 | ≥14 | ≥16 | ≥392 | 302-363 | |
| Stamping parts for aircraft (disks, baffles, labyrinths and socks). Hardening in air, 1100-1120 °C (exposure 8 h), air cooling + Tempering air with 990-1010 °C (exposure 4 h), air cooling + Ageing at 765-785 °C for 16 h, air cooling | ||||||
| - | ≥675 | ≥1100 | ≥15 | ≥16 | ≥392 | 294-341 |
| - | ≥705 | ≥1130 | ≥17 | ≥19 | ≥490 | 294-341 |
| Stamping parts for aircraft (disks, baffles, labyrinths and socks). Hardening in air, 1100-1120 °C (exposure 8 h), air cooling + Tempering air with 990-1010 °C (exposure 4 h), air cooling + Ageing at 765-785 °C for 16 h, air cooling + Ageing at 690-710 °C for 16-24 h, air cooling (or Aging at 740-760 °C for 8-16 h, air cooling) | ||||||
| - | ≥705 | ≥1130 | ≥13 | ≥15 | ≥343 | 302-363 |
| - | ≥725 | ≥1160 | ≥14 | ≥16 | ≥392 | 302-363 |
| Stamping parts for aircraft (disks, baffles, labyrinths and socks). Anneal at 890-910 °C, (excerpt 10 hours), air cooling + Tempering air with 1030-1050 °C (extract 2-6 h), air cooling + Ageing at 740-760 °C for 16 h, air cooling (or double aging 765-785 °C (exposure 8 h), air cooling + at 740-760 °C (16 h exposure), air cooling) | ||||||
| - | ≥705 | ≥1130 | ≥15 | ≥16 | ≥392 | 302-363 |
| - | ≥725 | ≥1160 | ≥17 | ≥19 | ≥490 | 302-363 |
Description mechanical marks
| Name | Description |
|---|---|
| Section | Section |
| sT|s0,2 | Yield strength or limit of proportionality with a tolerance for residual deformation of 0.2% |
| σB | Limit short-term strength |
| d5 | Elongation after rupture |
| y | The relative narrowing |
| kJ/m2 | Toughness |
