Alloy VT8

Designation

Name The value
Designation GOST Cyrillic ВТ8
Designation GOST Latin BT8
Transliteration VT8
By 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, 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
Bars and shapes 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 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%.

Mechanical properties

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