Alloy VT8
Alloy VT8M-1
Alloy VT32
Alloy VT35
Alloy VT4
Alloy VT41
Alloy VT5
Alloy VT5-1
Alloy VT6 (VT6sv.)
Alloy VT6C
Alloy VT6h
Alloy VT8
Alloy VT8-1
Alloy VT3-1
Alloy VT9
OT4 alloy
Alloy OT4-0
Alloy OT4-1
Alloy OT4-2
Alloy PT-1M
Alloy PT-3B
Alloy PT-7M
Alloy SPT-2
Alloy TC5
Alloy TC6
Alloy VT15
Alloy 14
Alloy 19
Alloy 27
Alloy 2B
Alloy 37
Alloy 3M
Alloy 40
Alloy 5B
Alloy AT3
Alloy AT6
Alloy VT14
Alloy VT25U
Alloy VT16
Alloy VT18
Alloy VT18U
Alloy VT2 (VT2sv.)
Alloy VT20
Alloy VT20-1 (VT20-1sv.)
Alloy VT20-2 (VT20-2sv.)
Alloy VT22
Alloy VT22I
Alloy VT23
Designation
| Name | The value |
|---|---|
| Designation GOST Cyrillic | ВТ8 |
| Designation GOST Latin | BT8 |
| Transliteration | VT8 |
| The chemical elements | ВTe8 |
Description
Alloy VT8 is used: for the manufacture of semi-finished products (sheets, strips, foils, strips, plates, bars, rods, profiles, tubes, forgings and forged blanks) by the strain, and bars; parts for various purposes, operating at temperatures up to +480 °C; parts of gas turbine aircraft engines (discs, vanes, low pressure compressor, mounting parts fan).
Note
Titanium alloy with high corrosion resistance. Alloy VT8 provides higher strength and heat resistant properties in comparison with rafting VT6 due to the high content of aluminum and silicon alloying. Alloy VT8 (and VT8−1 and VT8−1M) exceeds the alloys VT3−1 and VT9 heat stability, plasticity, workability and characteristics of fracture toughness. Double and isothermal annealing provide the best combination of properties; the content of b — phase in the annealed alloy to about 10%. Alloy thermally hardened.
A satisfactory alloy is deformed in the hot state. Technological properties during pressure treatment worse than that of alloy VT6.
Welding of alloy VT8 is not recommended.
Standards
| Name | Code | Standards |
|---|---|---|
| Non-ferrous metals, including rare metals, and their alloys | В51 | GOST 19807-91, OST 1 90000-70, OST 1 90013-81, OST 1 90197-89, OST 1 90002-86 |
| Bars | В55 | GOST 26492-85, OST 1 92020-82, OST 1 90266-86, OST 1 90173-75, OST 1 90107-73, OST 1 90006-86, TU 1-9-672-78 |
| Sectional and shaped rolling | В52 | OST 1 92039-75, OST 1 92051-76, OST 1 90101-73 |
Chemical composition
| Standard | C | Si | Fe | N | Al | Ti | Mo | O | Zr | H |
|---|---|---|---|---|---|---|---|---|---|---|
| OST 1 90013-81 | ≤0.1 | 0.2-0.4 | ≤0.3 | ≤0.05 | 5.8-7 | The rest | 2.8-3.8 | ≤0.15 | ≤0.5 | ≤0.015 |
Ti is the basis.
According to GOST 19807-91 and OST 1 90013-81 the total content of other impurities is ≤ 0.30%. The mass fraction of hydrogen is indicated for ingots. In the alloy, a partial replacement of molybdenum by tungsten in an amount not exceeding 0.3% is allowed. The total mass fraction of molybdenum and tungsten should not exceed the norms specified in the table for molybdenum. The mass fraction of chromium and manganese should not exceed 0.15% (in total). The mass fraction of copper and nickel should not be more than 0.10% (in total), including nickel not more than 0.08%.
According to OST 1 90013-81 in the semi-finished products of VT8 alloy, in addition to punching blades, disks and blanks thereof, the aluminum content is allowed up to 7.30%.
According to GOST 19807-91 and OST 1 90013-81 the total content of other impurities is ≤ 0.30%. The mass fraction of hydrogen is indicated for ingots. In the alloy, a partial replacement of molybdenum by tungsten in an amount not exceeding 0.3% is allowed. The total mass fraction of molybdenum and tungsten should not exceed the norms specified in the table for molybdenum. The mass fraction of chromium and manganese should not exceed 0.15% (in total). The mass fraction of copper and nickel should not be more than 0.10% (in total), including nickel not more than 0.08%.
According to OST 1 90013-81 in the semi-finished products of VT8 alloy, in addition to punching blades, disks and blanks thereof, the aluminum content is allowed up to 7.30%.
Mechanical characteristics
| Section, mm | σB, MPa | d5, % | d | y, % | kJ/m2, кДж/м2 | Brinell hardness number, MPa | HRC |
|---|---|---|---|---|---|---|---|
| The blades of aircraft engines is made by forging after double annealing (microgravity (Mg) is the projected area up to 20 cm2, small (M) - 20-250 cm2, midsize (C) - 250-550 cm2, bulk (K) - 550-1500 cm 2) | |||||||
| Мг, М | 980-1180 | ≥10 | - | ≥30 | ≥294 | 269-363 | 30-40.5 |
| The pressed bars for OST 1 92020-82. Annealing. The longitudinal samples | |||||||
| ≤60 | 1030-1226 | - | ≥9 | ≥30 | ≥294 | - | - |
| Forged discs and shafts after heat treatment OST 1 90197-89 all weight categories | |||||||
| - | ≥685 | - | - | - | - | - | - |
| The blades of aircraft engines is made by forging after double annealing (microgravity (Mg) is the projected area up to 20 cm2, small (M) - 20-250 cm2, midsize (C) - 250-550 cm2, bulk (K) - 550-1500 cm 2) | |||||||
| С, К | 980-1180 | ≥8 | - | ≥25 | ≥294 | 269-363 | 30-40.5 |
| The pressed bars for OST 1 92020-82. Annealing. The longitudinal samples | |||||||
| 60-100 | 1030-1226 | - | ≥9 | ≥25 | ≥294 | - | - |
| Forged discs and shafts after heat treatment OST 1 90197-89 all weight categories | |||||||
| - | ≥620 | - | - | - | - | - | - |
| The blades of aircraft engines is made by forging with the use of high-temperature thermomechanical treatment after aging (compact (M) - the projected area cm2 20-250, medium (C) - 250-550 cm2, bulk (K) - 550-1500 cm 2) | |||||||
| М, С, К | 1180-1380 | ≥6 | - | ≥22 | ≥245 | 321-415 | 36.5-45.5 |
| The pressed bars for OST 1 92020-82. Annealing. The longitudinal samples | |||||||
| 100 | ≥735 | - | - | - | - | - | - |
| Forgings weighing up to 200 kg after annealing | |||||||
| - | ≥667 | - | - | - | - | - | - |
| The blades of aircraft engines is made by forging with application of thermomechanical treatment after aging (microgravity (Mg) is the projected area up to 20 cm2, small (M) - 20-250 cm2, midsize (C) - 250-550 cm2, bulk (K) - 550-1500 cm 2) | |||||||
| Мг, М | 1080-1280 | ≥7 | - | ≥22 | ≥265 | 269-363 | 30-40.5 |
| Forgings weighing up to 200 kg after annealing | |||||||
| - | ≥540 | - | - | - | - | - | - |
| The blades of aircraft engines is made by forging with application of thermomechanical treatment after aging (microgravity (Mg) is the projected area up to 20 cm2, small (M) - 20-250 cm2, midsize (C) - 250-550 cm2, bulk (K) - 550-1500 cm 2) | |||||||
| С, К | 1030-1230 | ≥8 | - | ≥25 | ≥294 | 269-363 | 30-40.5 |
| Bars and rods, hot-rolled. Annealing | |||||||
| - | ≥736 | - | - | - | - | - | - |
| Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories) | |||||||
| ≤50 | 960-1160 | ≥10 | - | ≥25 | ≥343 | - | - |
| Bars and rods, hot-rolled. Annealing | |||||||
| - | ≥589 | - | - | - | - | - | - |
| Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories) | |||||||
| 50-100 | 960-1160 | ≥9 | - | ≥22 | ≥343 | - | - |
| 100-200 | 950-1150 | ≥8 | - | ≥22 | ≥343 | - | - |
| 200-500 | 940-1140 | ≥8 | - | ≥20 | ≥343 | - | - |
| Forgings weighing up to 200 kg after annealing | |||||||
| 101-150 | 932-1177 | ≥7 | - | ≥16 | ≥294 | 269-363 | - |
| 151-250 | 932-1177 | ≥6 | - | ≥16 | ≥294 | 269-363 | - |
| 100 | 981-1226 | ≥9 | - | ≥25 | ≥294 | 269-363 | - |
| Bars hot rolled autogenie ordinary quality GOST 26492-85 (longitudinal samples) | |||||||
| 10-12 | ≥980 | ≥8 | - | ≥20 | - | - | - |
| 100-150 | ≥930 | ≥6 | - | ≥15 | 198 | - | - |
| 12-100 | ≥980 | ≥8 | - | ≥20 | ≥294 | - | - |
| Bars hot rolled autogenie high-quality according to GOST 26492-85 (longitudinal samples) | |||||||
| 10-12 | 980-1230 | ≥9 | - | ≥30 | - | - | - |
| 100-150 | 930-1180 | ≥7 | - | ≥19 | ≥294 | - | - |
| 12-60 | 980-1230 | ≥9 | - | ≥30 | ≥294 | - | - |
| 60-100 | 980-1180 | ≥9 | - | ≥25 | ≥294 | - | - |
| Forged square bars and round after annealing | |||||||
| ≤150 | 932-1177 | ≥7 | - | ≥16 | ≥294 | 269-363 | - |
| 151-250 | 932-1177 | ≥6 | - | ≥16 | ≥294 | 269-363 | - |
| 961-1177 | ≥8 | - | ≥20 | ≥294 | 269-363 | - | |
Description mechanical marks
| Name | Description |
|---|---|
| Section | Section |
| σB | Limit short-term strength |
| d5 | Elongation after rupture |
| d | Elongation after rupture |
| y | The relative narrowing |
| kJ/m2 | Toughness |
| HRC | Rockwell hardness (indenter diamond spheroconical) |
