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High Temperature Cyclic Behaviour of Aerospace Materials - Room Temperature Validation Tests of Ti-6AL-4V

The cost of validating new materials and design methods is
placing increased emphasis on laboratory data for compo-
nent lifing and safety. In the aero gas turbine the use of higher
strength materials has led to the introduction of damage toler-
ant concepts, and the need for elevated temperature crack
growth data encompassing both complex loading and short
crack behaviour. Similarly the introduction of materials with
higher temperature capability has placed greater emphasis on
the role of creep and on studies of strain control fatigue
behaviour.

Within the family of AGARD nations, all are either manufac—
turers of or customers for advanced military engines. They
thus have a common need for accepted international stand-
ards for materials testing, data analysis and data presentation,
particularly as they relate to design, lifing and safety.

The member nations have a widespread collective involve-
ment with Materials Testing, and have already gone a long way
towards establishing standards for room temperature testing
through AGARD-8MP TX114, latterly SC33. The parallel
test programme described here, directed towards High Tem-
perature Cyclic Behaviour, was a logical extension of that
activity.

All laboratories involved with the activity have benefited from
the exchange of information and experience that has
occurred. Non participating laboratories will benefit from the
testing standards that have emerged, allowing for meaningful
data exchange to take place both within and between coun-
tries.

The overall objective of the full programme, of which the test-
ing of Ti-6Al-4V covered in this report forms part, is to
establish internationally accepted and agreed methods for
elevated temperature testing, data collection and data analy-
sis for aerospace materials, particularly with regard to crack
growth and low cycle fatigue.

Although the programme was initially designed for engine
disc materials, the methods will be applicable to other high
temperature materials and components. In particular the pro-
gramme will have relevance to the high temperature airframe
components which are seen as important for the next genera-
tion of high speed aircraft.