Alloy VT6 (Vt6sv.)

Designation

Name	The value
Name	The value
Designation GOST Cyrillic	ВТ6
Designation GOST Latin	BT6
Transliteration	VT6
By chemical elements	ВTe6

Name	The value
Name	The value
Designation GOST Cyrillic	ВТ6св.
Designation GOST Latin	BT6cb.
Transliteration	VT6sv
By chemical elements	ВTe6св.

Description

Alloy VT6 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; welding wire with a diameter of 1.6−7.0 mm; shtampovannyh parts, long operating at temperatures up to +400−450 °C; large-size welded and modular designs of aircraft; cylinders operating under internal pressure in a wide temperature range from -196 °C to +450 °C, and a number of other constructive elements.

Note

Alloy (a+b)-class. Aluminum alloys of the system Ti-Al-V improves the strength and heat resisting properties, and vanadium is among the few alloying elements in titanium, which increases not only the strength properties, but also plasticity.
Along with high specific strength alloys of this type are less sensitive to hydrogen as compared with alloys OT4 and OT4−1, a low propensity to salt corrosion and good workability.
Alloy well deformed in the hot state. The alloy is welded by all traditional welding processes, including diffusion. When welding EBW weld strength almost equal to the strength of the base material, which distinguishes this from alloy VT22.

Standards

Name	Code	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, Tuop 1-809-112-2010
Sheets and strips	В53	GOST 22178-76, GOST 23755-79, OST 1 90218-76, OST 1 90024-94, TU 1-5-361-75
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
Welding and cutting metals. Soldering, riveting	В05	OST 1 90015-77
Bars and shapes	В52	OST 1 92039-75, OST 1 92051-76, OST 1 92064-77, OST 1 90100-73

Chemical composition

Standard	C	Si	Fe	N	Al	V	Ti	O	Zr	H
Standard	C	Si	Fe	N	Al	V	Ti	O	Zr	H
GOST 19807-91	≤0.1	≤0.1	≤0.6	≤0.05	5.3-6.8	3.5-5.3	Rest	≤0.2	≤0.3	≤0.015
OST 1 90015-77	≤0.05	≤0.1	≤0.15	≤0.04	3.5-4.5	2.5-3.5	Rest	≤0.12	-	≤0.003

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. 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%.
OST 1 90013-81 for the manufacture of semi-finished alloy VT6 for technical documentation, which provides a minimum level of tensile strength 932 MPa (95 kgf / mm ²⁾ of aluminum and vanadium contents be respectively not more than 7.00% and 5.50% and the iron content not more than 0.50%. At the request of the customer, the supply of VT6 alloy is produced with an iron content of not more than 0.30%.
According to OST 1 90015-77 the chemical composition is given for alloy VT6sv. material of the welding wire. The amount of other impurities is ≤ 0.30%.

Mechanical properties

Section, mm	σ_U, MPa	d₅, %	d	y, %	KCU, kJ/m²	HB, MPa	HRC
Section, mm	σ_U, MPa	d₅, %	d	y, %	KCU, kJ/m²	HB, MPa	HRC
Rolled sheet after annealing (samples across the direction of rolling)
1-10.5	883-1080	≥8	-	-	-	-	-
The pressed bars for OST 1 92020-82. Annealing. The longitudinal samples
100	902-1079	-	≥10	≥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 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	930-1120	≥10	-	≥30	≥343	255-341	28-38.5
The pressed bars for OST 1 92020-82. Annealing. The longitudinal samples
100	≥637	-	-	-	-	-	-
The blades of aircraft engines is made by forging after 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	930-1120	≥9	-	≥25	≥343	255-341	28-38.5
The blades of aircraft engines is made by forging with the use of high-temperature 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	285-388	35-43.5
С, К	1030-1230	≥8	-	≥25	≥294	285-388	35-43.5
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	930-1180	≥10	-	≥30	≥343	255-341	28-38.5
С, К	930-1180	≥9	-	≥25	≥343	255-341	28-38.5
Plate in the delivery condition according to GOST 23755-79. Annealing (samples transverse)
11-60	880-1080	-	≥6	≥16	≥294	-	-
60-100	835-1030	-	≥6	≥12	≥294	-	-
Plate on OST 1 90024-94 in the delivery condition. Samples heat-treated (transverse)
100-160	885-1080	-	≥6	≥12	≥294	-	-
11-60	885-1080	-	≥6	≥16	≥294	-	-
60-100	885-1080	-	≥6	≥12	≥294	-	-
Forged discs and shafts after heat treatment OST 1 90197-89 (samples cut in Cordova direction; specified blank weight categories)
≤50	930-1130	≥10	-	≥30	≥392	-	-
50-100	930-1130	≥10	-	≥25	≥392	-	-
100-200	900-1130	≥9	-	≥25	≥392	-	-
Forgings weighing up to 200 kg after annealing
101-250	834-1050	≥6	-	≥20	≥294	255-341	-
100	903-1080	≥10	-	≥30	≥294	255-341	-
The welding wire in degassed and etched condition delivery
1.6-7	≥667	-	≥12	-	-	-	-
Bars hot rolled quenched and aged normal-quality according to GOST 26492-85 (longitudinal samples)
10-12	≥1080	≥4	-	≥12	-	-	-
12-100	≥1080	≥4	-	≥12	≥196	-	-
Bars hot rolled quenched and aged high-quality according to GOST 26492-85 (longitudinal samples)
10-12	≥1080	≥6	-	≥20	-	-	-
12-60	≥1080	≥6	-	≥20	≥294	-	-
60-100	≥1080	≥6	-	≥20	≥245	-	-
Bars hot rolled autogenie ordinary quality GOST 26492-85 (longitudinal samples)
10-12	≥885	≥8	-	≥20	-	-	-
100-150	≥835	≥6	-	≥15	≥245	-	-
12-100	≥885	≥8	-	≥20	≥245	-	-
Bars hot rolled autogenie high-quality according to GOST 26492-85 (longitudinal samples)
10-12	905-1050	≥10	-	≥30	-	-	-
100-150	835-1050	≥6	-	≥20	≥294	-	-
12-60	905-1050	≥10	-	≥30	≥392	-	-
60-100	905-1050	≥10	-	≥25	≥294	-	-
Bars and rods, hot-rolled. Quenching + aging
≤100	≥1080	≥6	-	≥20	≥245	321-388	-
10-60	≥1080	≥6	-	≥20	≥294	321-388	-
Bars and rods, hot-rolled. Annealing
≥110	835-1050	≥8	-	≥25	≥343	255-341	-
65-100	900-1050	≥10	-	≥27	≥294	255-341	-
10-60	903-1050	≥10	-	≥30	≥392	255-341	-
Forged square bars and round after annealing
140-250	834-1050	≥6	-	≥20	≥294	255-341	-
	883-1050	≥7	-	≥25	≥294	255-341	-

Description mechanical marks

Name	Description
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)
Temperature	Е, HPa	r, kg/m³	l, W/(m · °C)	R, Mr. · m	a, 10^-6 1/°C	С, J/(kg · °C)
20	115	4430	837	1600	-	-
100	-	-	921	1820	84	-
200	-	-	1088	2020	87	586
300	-	-	117	2120	9	67
400	-	-	1256	2140	10	712
500	-	-	1382	-	-	795
600	-	-	1549	-	-	879

A description of the physical symbols

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

Technological properties

Name	The value
Name	The value
Weldability	without restrictions