Near-beta titanium alloy for high strength applications and methods for manufacturing the same
A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7% aluminum, 4.8 to 5.2% vanadium, 0.7 to 0.9% iron, 4.6 to 5.3% molybdenum, 2.0 to 2.5% chromium, and 0.12 to 0.16% oxygen with balance titanium and incidental impurities is provided. An aviation system component comprising the high strength near-beta titanium alloy, and a method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications are also provided.
1. A titanium alloy consisting essentially of, in weight %, 5.3 to 5.7 aluminum, 4.8 to 5.2 vanadium, 0.7 to 0.9 iron, 4.6 to 5.3 molybdenum, 2.0 to 2.5 chromium, and 0.12 to 0.16 oxygen and optionally one or more additional elements selected from N, C, Nb, Sn, Zr, Ni, Co, Cu and Si wherein each additional element is present in an amount of less than 0.1% and the total content of additional elements is less than 0.5 weight %, and the balance titanium.
2. The titanium alloy of claim 1 having a ratio of beta isomorphous to beta eutectoid stabilizers of about 1.4, wherein the ratio of beta isomorphous to beta eutectoid stabilizers is defined as:
β
ISO
β
EUT
=
Mo
+
V
1.5
Cr
0.65
+
Fe
0.35
.
3. The titanium alloy of claim 1 , wherein the weight % of the aluminum is about 5.5.
4. The titanium alloy of claim 1 , wherein the weight % of the vanadium is about 5.0.
5. The titanium alloy of claim 1 , wherein the weight % of the iron is about 0.8.
6. The titanium alloy of claim 1 , wherein the weight % of the molybdenum is about 5.0.
7. The titanium alloy of claim 1 , wherein the weight % of the chromium is about 2.3.
8. The titanium alloy of claim 1 , wherein the weight % of the oxygen is about 0.14.
9. An aviation system component which is a landing gear or a fastener and which comprises an alloy according to claim 1 .
10. A method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications, comprising:
providing a titanium alloy consisting essentially of, in weight %, 5.3 to 5.7 aluminum, 4.8 to 5.2 vanadium, 0.7 to 0.9 iron, 4.6 to 5.3 molybdenum, 2.0 to 2.5 chromium, and 0.12 to 0.16 oxygen and optionally one or more additional elements selected from N, C, Nb, Sn, Zr, Ni, Co, Cu and Si wherein each additional element is present in an amount of less than 0.1% and the total content of additional elements is less than 0.5 weight %, and the balance titanium;
performing a solution heat treatment of the titanium alloy at a subtransus temperature; and
performing precipitation hardening of the titanium alloy.
11. The method of claim 10 , further comprising vacuum arc remelting the alloy.
12. The method of claim 10 , further comprising forging and rolling the titanium alloy below the beta transformation temperature.
13. A method for manufacturing an aviation system component which is a landing gear or a fastener which method comprises the method of claim 10 .