Ti 6242

Titanium 6-2-4-2 is a near-alpha high strength titanium alloy that shows a good combination of tensile strength, creep strength, and toughness. It shows long term stability at temperatures up to 800°F (425°C). Up to 0.1% of silicon is frequently added to improve the creep resistance of this alloy. Ti 6-2-4-2 is produced by primary melting under vacuum (VAR), electron beam (EB) melting, or plasma arc cold hearth melting (PAM). Primary melting is followed by single or double vacuum arc remelting (VAR).

Advanced Inventory Size Ranges for 6242

Type	Size Range	Specifications	Get a Quote
Build Platform	0.50" - 5.00"	AMS 4919, ASTM B265, UNS R54620	Get a Quote

Characteristics of Ti 6-2-4-2

Stress relief annealing is done from 900 - 1,300°F (482 - 704°C) followed by air cool or slow cool. For bars and forgings, material is solution treated from 1,650 - 1,750°F (899 - 954°C) for 1 hour and air cool. This is followed by stabilization at 1,100°F (593°C) for 8 hours and air cool. Small increases in tensile strength may be obtained by solution treating and aging, but this is at the expense of creep strength compared to the annealed and stabilized product. Ti 6-2-4-2 can be subject to hydrogen contamination during improper pickling and by oxygen, nitrogen, and hydrogen pickup during forging, heat treating, brazing, etc. This contamination results in a deterioration in ductility which adversely affects notch sensitivity and forming characteristics.

Working with Ti 6-2-4-2

This alloy can be machined using practices for austenitic stainless steels using slow speeds, heavy feeds, rigid tooling, and large amounts of non-chlorinated cutting fluid. Ti 6-2-4-2 is easily welded if proper precautions are taken to prevent oxygen, nitrogen, and hydrogen contamination. Fusion welding can be done in inert gas filled chambers or using inert gas shielding of the molten weld metal and the adjacent heated zones using a trailing shield. Spot, seam, and flash welding can be performed without resorting to protective atmospheres.

Other industry standards we comply with:

Common Trade Names

Industry Applications for 6242

Jet Engine Components
Turbine Discs & Blades
Gas Turbine Compressors
Afterburners
Landing Gear Systems
Fasteners

Chemical Composition

Chemical Composition Percentage of Ti 6242
	Element	Percent by Weight Min	Percent by Weight Max
Al	Aluminum	5.5	6.5
Sn	Tin	1.8	2.2
Zr	Zirconium	3.6	4.4
Mo	Molybdenum	1.8	2.2
Si	Silicon	0.06	0.13
Fe	Iron	-	0.25
O	Oxygen	-	0.15
C	Carbon	-	0.08
N	Nitrogen	-	0.05
H	Hydrogen	0.010	0.0125
Ti	Titanium	-	Remainder

Physical Properties

Property	Value
Density	0.164 lb/in³ (4.54 gm/c³)
Melting Range	2,890-3,120° F (1,588 - 1,716° C)
Beta Transus Temperature	1,825°F (± 25 F°); (995°C (± 15 C°))
Specific Heat	Btu/lb.-°F (460 J/kg)

Mechanical Properties

Property	Value
Hardness (Duplex Annealed Condition)	32-36 HRC

Additional Info

A Brief History of Ti 6242

Ti‑6242 emerged in the 1960s–1970s, during a period when aerospace propulsion systems were rapidly advancing and pushing materials far beyond the capabilities of early titanium alloys like Ti‑6Al‑4V. Engineers needed a titanium alloy that could maintain strength, creep resistance, and stability at elevated temperatures—specifically in the 900–1100°F (480–595°C) range. This demand led to the development of a family of near‑alpha titanium alloys, with Ti‑6242 becoming one of the most successful and widely adopted. It quickly became known as a workhorse alloy for high‑temperature aerospace components.

How Ti 6242 Was Developed

Ti‑6242 was engineered by adjusting the balance of alpha‑stabilizing and beta‑stabilizing elements to create a titanium alloy that could:

Maintain strength at elevated temperatures
Resist creep and fatigue
Offer good oxidation resistance
Provide stable microstructure under thermal cycling

The result was a near‑alpha alloy with excellent high‑temperature performance and good forgeability—ideal for rotating and structural components in jet engines.

Early Applications of Ti 6242

Once introduced, Ti‑6242 quickly found its way into high‑temperature aerospace components where traditional titanium alloys could not survive. Early use cases included compressor discs and blades for jet engines, afterburner components, hot-section structural parts, airframe components, and forged rotating parts. Its ability to maintain mechanical integrity at temperatures above Ti‑6Al‑4V’s limits made it a breakthrough alloy for next‑generation propulsion systems.

How Ti 6242 is Used Today

Ti‑6242 remains a major aerospace alloy and continues to be used in modern engines and high‑performance systems.

Jet engine compressor components (discs, blades, seals, spacers)
Rotating engine hardware
High‑temperature airframe structures
Afterburner and exhaust components
Industrial gas turbine parts
High‑performance motorsport components
Spacecraft structures requiring strength at elevated temperatures

Its combination of high‑temperature strength, fatigue resistance, and oxidation resistance keeps it relevant even as newer titanium alloys emerge.

Your Trusted Supplier of Ti 6242

UPM Advanced Solutions supplies build platform material in sizes 0.50" - 5.00". This product often is used in gas turbine engines for compressor blades, discs, and impellers. It is also used in afterburner structures and airframe skin applications.

Product FAQs

Ti 6242 has much better creep resistance, high strength retention at elevated temperatures, greater thermal stability, and was designed for hot-section engine components.

Ti‑6242 performs reliably in the 900–1100°F range, depending on the application and heat‑treat condition. This makes it ideal for compressor components and other hot‑section hardware.

Yes, Ti 6242 responds well to heat treatment, which can improve strength, creep resistance, and fatigue performance. Solution treatment and aging (STA) conditions are commonly used in aerospace components.