Alloy VT3-1

Designation

Name The value
Designation GOST Cyrillic ВТ3-1
Designation GOST Latin BT3-1
Transliteration VT3-1
By chemical elements ВTe3-1

Description

Alloy VT3−1 is 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 method of deformation, and also ingots; forged and the stamp-Sunnah parts operating at temperatures up to +400 °C (up to 6000 hours) and up to +450 °C (up to 2000 hours); aircraft parts, aircraft engines and parts such as valves, ushkovyh bolts, parts of the control system.

Note

Alloy VTZ-1 the system Ti-Al-Mo-Cr-Fe-Si refers to high-strength (a+b)-alloys of the martensitic class. Aluminum alloy VTZ-1 strengthens the a — and b-phase reduces the density of the alloy. Macrodatabases b-stabilizers chromium, iron and silicon strengthens the a — and b-phase, and enhance the strength and heat resisting properties at moderate temperatures. Molybdenum increases the strength and heat resisting properties of the alloy, but makes a collapse of the eutectic b-phase, improving the thermal stability.
Alloy well deformed in the hot state; it produces rolled, extruded and forged bars, rolled and extruded profiles, various forgings, strip, plate, rolled rings, in the experimental procedure — pipe. Alloy welded satisfactorily by all types of welding, used for titanium. After welding it is necessary to conduct annealing to restore ductility of a welded joint.

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 90201-75, 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 90098-73, TU 1-9-975-76
Tubes of non-ferrous metals and alloys В64 TU 1-5-127-73
Steel pipes and fittings to them В62 TU 14-3-1514-87

Chemical composition

Standard C Cr Si Fe N Al Ti Mo O Zr H
GOST 19807-91 ≤0.1 0.8-2 0.15-0.4 0.2-0.7 ≤0.05 5.5-7 Rest 2-3 ≤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 grade VT3-1, designed for the manufacture of stamping blades and bladed billet, the upper limit of the mass fraction of aluminum should be no more than 6.80%. 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 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, % 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 1030-1230 ≥9 - ≥27 ≥294 269-363 30-40.5
Forged discs and shafts after heat treatment OST 1 90197-89 all weight categories
- ≥735 - - - - - -
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 1030-1230 ≥8 - ≥25 ≥294 269-363 30-40.5
Forged discs and shafts after heat treatment OST 1 90197-89 all weight categories
- ≥635 - - - - - -
The blades of aircraft engines is made by forging after isothermal 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, osbornemedia (OK) - over 1500 cm2)
Мг, М 980-1180 ≥10 - ≥30 ≥294 269-363 30-40.5
Forgings weighing up to 200 kg after annealing
- ≥706 - - - - - -
The blades of aircraft engines is made by forging after isothermal 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, osbornemedia (OK) - over 1500 cm2)
С, К, ОК 980-1180 ≥10 - ≥27 ≥294 269-363 30-40.5
Forgings weighing up to 200 kg after annealing
- ≥638 - - - - - -
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 1030-1230 ≥9 - ≥27 ≥294 269-376 30-42
Bars and rods, hot-rolled. Annealing
- ≥687 - - - - - -
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
- ≥638 - - - - - -
Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories)
≤25 960-1160 ≥10 - ≥25 ≥294 - -
The pressed bars for OST 1 92020-82. Annealing. The longitudinal samples
100 981-1177 - ≥10 ≥30 ≥294 - -
Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories)
25-50 940-1140 ≥10 - ≥25 ≥294 - -
The pressed bars for OST 1 92020-82. Annealing. The longitudinal samples
100 ≥735 - - - - - -
Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories)
50-100 940-140 ≥9 - ≥22 ≥294 - -
100-200 940-1140 ≥8 - ≥22 ≥294 - -
200-500 940-1140 ≥8 - ≥20 ≥294 - -
Forgings weighing up to 200 kg after annealing
101-250 932-1177 ≥8 - ≥20 ≥294 269-363 -
100 981-1177 ≥10 - ≥25 ≥294 269-363 -
The bars as supplied on OST 1 90201-75
- 980-1226 ≥12 - ≥35 - - -
Bars hot rolled quenched and aged high-quality according to GOST 26492-85 (longitudinal samples)
10-12 ≥1180 ≥6 - ≥20 - - -
12-40 ≥1180 ≥6 - ≥20 ≥196 - -
40-60 ≥1180 ≥6 - ≥16 ≥176 - -
Bars hot rolled autogenie ordinary quality GOST 26492-85 (longitudinal samples)
10-12 ≥930 ≥8 - ≥20 - - -
100-150 ≥930 ≥6 - ≥15 ≥245 - -
12-100 ≥930 ≥8 - ≥20 ≥294 - -
Bars hot rolled autogenie high-quality according to GOST 26492-85 (longitudinal samples)
10-12 980-1230 ≥10 - ≥30 - - -
100-150 930-1180 ≥8 - ≥20 ≥294 - -
12-60 980-1230 ≥10 - ≥30 ≥294 - -
60-100 980-1180 ≥10 - ≥25 ≥294 - -
Forged square bars and round after annealing
140-250 932-1177 ≥8 - ≥20 ≥294 269-363 -
961-1177 ≥9 - ≥22 ≥294 269-363 -
Stamping. Quenching + aging
1150-1220 10-12 - 32-48 - - -

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)

Physical characteristics

Temperature Е, HPa r, kg/m3 l, W/(m · °C) R, Mr. · m a, 10-6 1/°C С, J/(kg · °C)
20 115 4500 801 1360 - -
100 - - 879 - 86 -
200 - - 1004 - 98 502
300 - - 113 - 103 544
400 - - 1292 - 109 628
500 - - 1424 - 114 67
600 - - 1549 - - 712

A description of the physical symbols

Name Description
Е The normal elasticity modulus
l Coefficient of thermal conductivity
R UD. the resistivity
С Specific heat

Technological properties

Name The value
Weldability limited weldability