Description
Ti-8Al-1Mo-1V alloy (UNS R54810) is a near alpha alloy with aluminum being the alpha stabilizer, and the additions of Mo, V and Fe resulting in small amounts of beta. The alloy is intended primarily for use at elevated temperatures, has good creep strength and good weldability, and possesses the lowest density of any titanium-base alloy.
Ti-8-1-1 alloy is used in the annealed condition, and special duplex annealing procedures have been developed for thick sections, such as bars and forgings. Typical applications are airframe and jet engine parts requiring high strength, superior creep strength a good stiffness-to-density ratio, and toughness. Ti-8Al-1Mo-1V is primarily used in aircraft engine applications. The alloy is available as wire (for welding), bar, billet, sheet, plate, extrusions, and forgings.
Beta Transus Temperature: 1,900°F (1,038°C)

Chemistry Requirements

Minimum Tensile Properties

Typical Tensile Properties

Principal Design Features
One of the most widely used precipitation hardening grades in the business. While soft and ductile in the solution annealed condition, it is capable of high properties with a single precipitation or aging treatment. Characterized by good corrosion resistance, high harness, toughness and strength.
Features: Designed for creep resistance up to 450°C, used primarily in engine applications such as forged compressor blades and disks. This alloy has a relatively high tensile modulus to density ratio compared to most commercial titanium alloys.
Machinability
Long, gummy chips characterize this alloys machinability. It can be machined in the annealed condition, however condition H1150M will yield best results. Post machining solution treatment of parts will be required prior to final hardening if machining in this condition.
Welding
Successfully welded by common fusion and resistance methods, this alloy should not be joined by oxy acetylene welding. AWS E/ER630 filler metal is recommended if required. TI 8-1-1 alloy can be successfully welded by the inert gas shielded fusion and resistance-welding processes. Any subsequent stress relief annealing should avoid the temperature range of 1,000 - 1,200°F (538 - 649°C), which would result in a loss of fracture toughness.
Forging
Soak for 1 hour at 2150 F (1177 C) prior to forging. Do not work below 1850 F (1010 C). Post-work solution treatment is required prior to final hardening. TI 8-1-1 alloy is finish-forged from 1,850°F (1,010°C) with a minimum finishing temperature of 1,650°F (899°C). Minimum reductions of about 35% in the alpha - beta range are recommended to obtain specification properties.

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