Alloy ВТ18У
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 | ВТ18У |
| Designation GOST Latin | BT18U |
| Transliteration | VT18U |
| The chemical elements | ВTe18У |
Description
Alloy ВТ18У used: for the production of bars, rods, forgings and stampings, sheet metal; parts of gas turbine engines operating in the temperature range of +550−600 °C.
Note
Pseudo α-alloy ВТ18У different from ВТ18 lower content of aluminum and zirconium, and the additional alloying with tin. In this regard, he is somewhat smarter ВТ18. At the high-temperature properties of the alloy ВТ18У is not inferior to the alloy ВТ18 and is recommended for the same operating conditions as the alloy ВТ18.
Standards
| Name | Code | Standards |
|---|---|---|
| Bars | В55 | OST 1 90006-86, TU 1-92-51-77 |
| Non-ferrous metals, including rare metals, and their alloys | В51 | OST 1 90013-81, OST 1 90197-89, OST 1 90002-86 |
Chemical composition
| Standard | C | Si | Fe | N | Al | Ti | Mo | Sn | Nb | O | Zr | H |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| OST 1 90013-81 | ≤0.1 | 0.1-0.25 | ≤0.2 | ≤0.04 | 6.2-7.3 | The rest | 0.4-1 | 2-3 | 0.5-1.5 | ≤0.14 | 3.5-4.5 | ≤0.015 |
Ti is the basis.
According to OST 1 90013-81 the total content of other impurities is ≤ 0.30%. A partial replacement of molybdenum by tungsten in an amount not exceeding 0.30% is allowed. The total content of molybdenum and tungsten should not exceed the norms specified in the table for molybdenum. The total content of copper and nickel in an amount not exceeding 0.10% is allowed, including nickel not more than 0.080%. The total content of chromium and manganese in an amount not exceeding 0.15% is allowed.
According to OST 1 90013-81 the total content of other impurities is ≤ 0.30%. A partial replacement of molybdenum by tungsten in an amount not exceeding 0.30% is allowed. The total content of molybdenum and tungsten should not exceed the norms specified in the table for molybdenum. The total content of copper and nickel in an amount not exceeding 0.10% is allowed, including nickel not more than 0.080%. The total content of chromium and manganese in an amount not exceeding 0.15% is allowed.
Mechanical characteristics
| Section, mm | σB, MPa | d5, % | y, % | kJ/m2, кДж/м2 | Brinell hardness number, MPa | HRC |
|---|---|---|---|---|---|---|
| The blades of aircraft engines is made by forging after annealing (microgravity (Mg) is the projected area up to 20 cm2, small (M) - 20-250 cm2) | ||||||
| Мг, М | 930-1130 | ≥10 | ≥27 | ≥245 | 255-341 | 28-38.5 |
| Forged discs and shafts after heat treatment OST 1 90197-89 all weight categories | ||||||
| - | ≥560 | - | - | - | - | - |
| The blades of aircraft engines is made by forging with the use of thermo-mechanical processing and forging in isothermal conditions, including the conditions of superplasticity after aging (microgravity (Mg) is the projected area up to 20 cm2, small (M) - 20-250 cm2) | ||||||
| Мг, М | 930-1130 | ≥10 | ≥25 | ≥245 | 255-341 | 28-38.5 |
| Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories) | ||||||
| ≤50 | 910-1110 | ≥7 | ≥15 | ≥225 | - | - |
| 50-100 | 980-1080 | ≥6 | ≥14 | ≥225 | - | - |
Description mechanical marks
| Name | Description |
|---|---|
| Section | Section |
| σB | Limit short-term strength |
| d5 | Elongation after rupture |
| y | The relative narrowing |
| kJ/m2 | Toughness |
| HRC | Rockwell hardness (indenter diamond spheroconical) |
