Alloy VT9
Designation
| Name |
The value |
| Designation GOST Cyrillic |
ВТ9 |
| Designation GOST Latin |
BT9 |
| Transliteration |
VT9 |
| The chemical elements |
ВTe9 |
Description
Alloy VT9 used: for the manufacture of semi-finished products (sheets, strips, foils, strips, plates, bars, rods, profiles, pipe shells and pipe, forgings and forged blanks) by the strain, and bars; parts, operating at temperatures up to +500 °C; parts of gas turbine engines (discs, blades) and other parts of the compressor.
Note
Titanium alloy with high corrosion resistance. VT9 alloy provides higher strength and heat resistant properties in comparison with rafting VT6 due to the high content of aluminum and silicon alloying.
Double annealing provides an optimal combination of mechanical properties; the content of β-phase after annealing of about 10%. The alloy is thermally hardened by quenching and aging.
A satisfactory alloy is deformed in the hot state. Technological properties during pressure treatment worse than that of alloy VT6.
Welding is not recommended. Mainly used in turbine engine parts (discs, blades) and other parts of the compressor.
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 90266-86, OST 1 90173-75, OST 1 90107-73, OST 1 90006-86 |
| Sectional and shaped rolling |
В52 |
OST 1 92039-75, OST 1 92051-76, OST 1 90104-73 |
| Pipes from non-ferrous metals and alloys |
В64 |
TU 1-5-127-73 |
| Pipes steel and connecting parts to them |
В62 |
TU 14-3-566-77 |
Chemical composition
| Standard |
C |
Si |
Fe |
N |
Al |
Ti |
Mo |
O |
Zr |
H |
| OST 1 90013-81 |
≤0.1 |
0.2-0.35 |
≤0.25 |
≤0.05 |
5.8-7 |
The rest |
2.8-3.8 |
≤0.15 |
1-2 |
≤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%.
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 and forging in isothermal conditions, including the conditions of superplasticity 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 |
1030-1230 |
≥10 |
≥30 |
≥294 |
269-363 |
30-40.5 |
| Forged discs and shafts after heat treatment OST 1 90197-89 all weight categories |
| - |
≥685 |
- |
- |
- |
- |
- |
| The blades of aircraft engines is made by forging and forging in isothermal conditions, including the conditions of superplasticity 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 |
1030-1230 |
≥9 |
≥25 |
≥294 |
269-363 |
30-40.5 |
| Forgings weighing up to 200 kg after annealing |
| - |
≥687 |
- |
- |
- |
- |
- |
| 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) |
|
1180-1380 |
≥6 |
≥22 |
≥245 |
321-415 |
36.5-45.5 |
| Bars and rods, hot-rolled. Annealing |
| - |
≥687 |
- |
- |
- |
- |
- |
| 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) |
| С, К |
1180-1380 |
≥6 |
≥17 |
≥196 |
321-415 |
36.5-45.5 |
| 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 |
≥245 |
269-363 |
30-40.5 |
| С, К |
1060-1280 |
≥8 |
≥25 |
≥245 |
269-363 |
30-40.5 |
| Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories) |
| ≤50 |
1030-1230 |
≥8 |
≥22 |
≥294 |
- |
- |
| 50-200 |
1010-1210 |
≥8 |
≥20 |
≥245 |
- |
- |
| Forgings weighing up to 200 kg after annealing |
| 101-150 |
981-1226 |
≥6 |
≥14 |
≥294 |
269-363 |
- |
| 151-250 |
932-1226 |
≥6 |
≥14 |
≥294 |
269-363 |
- |
| 100 |
1030-1226 |
≥9 |
≥25 |
≥294 |
269-363 |
- |
| Bars hot rolled autogenie ordinary quality GOST 26492-85 (longitudinal samples) |
| 10-12 |
≥980 |
≥7 |
≥16 |
- |
- |
- |
| 100-150 |
≥930 |
≥6 |
≥15 |
≥196 |
- |
- |
| 12-100 |
≥980 |
≥7 |
≥16 |
≥245 |
- |
- |
| Bars hot rolled autogenie high-quality according to GOST 26492-85 (longitudinal samples) |
| 10-12 |
1030-1230 |
≥9 |
≥30 |
- |
- |
- |
| 100-150 |
980-1230 |
≥7 |
≥16 |
≥294 |
- |
- |
| 12-50 |
1030-1230 |
≥9 |
≥30 |
≥294 |
- |
- |
| 50-100 |
1030-1230 |
≥9 |
≥25 |
≥294 |
- |
- |
| Forged square bars and round after annealing |
| ≤150 |
981-1226 |
≥6 |
≥14 |
≥294 |
269-363 |
- |
| 151-250 |
932-1177 |
≥6 |
≥14 |
≥294 |
269-363 |
- |
|
1000-1226 |
≥7 |
≥16 |
≥294 |
269-363 |
- |
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) |
Technological properties
| Name |
The value |
| Weldability |
without restrictions |
