Alloy VT9

Designation

Name The value
Designation GOST Cyrillic ВТ9
Designation GOST Latin BT9
Transliteration VT9
By 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, 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
Bars and shapes В52 OST 1 92039-75, OST 1 92051-76, OST 1 90104-73
Tubes of non-ferrous metals and alloys В64 TU 1-5-127-73
Steel pipes and fittings 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 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 properties

Section, mm σU, MPa d5, % y, % KCU, kJ/m2 HB, 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
σU Limit short-term strength
d5 Elongation after rupture
y The relative narrowing
KCU Toughness
HB Brinell hardness number
HRC Rockwell hardness (indenter diamond spheroconical)

Technological properties

Name The value
Weldability without restrictions