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	σ_U, 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
σ_U	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