Authors: Theodore M Besmann
Publish Date: 2009/04/01
Volume: 44, Issue: 7, Pages: 1661-1663
Abstract
The drive for greater efficiency in propulsion and industrial/power production machinery has pushed metallurgists to develop ever better alloys and taken existing metallic components to their reliability threshold Nowhere is that better illustrated than in gas turbine engine materials The nickelbased superalloys currently in use for the most demanding areas of the engines melt at 1230–1315 °C and yet see combustion environments ~1600 °C The result is that these components require thermal protection to avoid failure from phenomena such as melting creep oxidation thermal fatigue and so on 1 The stakes are high as the equipment must remain reliable for thousands of takeoffs and landings for aircraft turbine engines and at least 40000 h of operation in power generating landbased gas turbines 2 3 The most critical items that see both the greatest temperatures and experience the highest stresses are the hotsection components particularly the high pressure turbine
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