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	σ_U, 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
σ_U	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