Abstract: A rotating or moving metal component such as a blade for a gas turbine engine is made from a composite bar of titanium alloy with the sides of the bar having a surface layer of e.g. nickel which is less likely to ignite in particle form or by frictional heating when present in oxygen or air. After the surface layer has been bonded to the titanium alloy it is then parted to provide sections which extend perpendicularly to the plane of the surface layers. Each parted section may then be machined into a blade with the nickel portion forming the tip of the blade. Alternatively, each parted section may itself form the blade tip by attachment on its titanium alloy side to a blade stem.

Abstract: A weldable titanium alloy particularly intended for use at high temperatures and under conditions of high stress in aircraft engines, the alloy having the composition 5.6% aluminium, 4% tin, 4% zirconium, 1% niobium, 0.25% molybdenum, 0.5% silicon, 0.05% carbon, optionally containing 0.2% tungsten and being used in the heat treated condition. The heat treatment would normally comprise a solution treatment above the beta transus, typically at 1080.degree. C., and an ageing or stress relieving treatment at a temperature of approximately 650.degree. C. for approximately 24 hours.

Abstract: A high strength titanium alloy capable of being used at elevated temperatures, the alloy containing 3.5-5.65% aluminium, 3.0-8.1% tin, with a total aluminium equivalent in the range 6.1-6.8%, 4.5-7.5% zirconium, 1.5-3% molybdenum, 0.2-0.6% silicon, balance titanium apart from incidental impurities, the alloy having good hardenability and having uniform hardenability throughout its depth, the alloy being weldable, resistant to crack propagation and having a good balance of properties suitable for use in applications requiring high strength at elevated temperatures.

Abstract: A heat treatment process to improve the strength of weldable near alpha titanium alloys comprising solution treating the alloy in the beta field and stress relief treating the alloy at two different temperatures, one of which is at 535.degree. C..+-.100.degree. C., particularly suitable for the titanium alloy containing 5.5% aluminium, 3.5% tin, 3% zirconium, 1% niobium, 0.25% molybdenum, 0.3% silicon.