The practicability of using ceramals with comparatively low strategic material content for the blades of aircraft turbines was determined in an experimental investigation. Four blade root configurations were examined.nThe most favorable results were obtained for ceramal turbine blades with single serration interlock and dovetail root configurations. Six of the interlock types were operated in a J33-A-33 engine for 68 hours, 23 minutes at rated service speed and six of the dovetail types were operated for 58 hours, 28 minutes at rated speed. This result confirms the conclusions of previous static design studies.
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