Preliminary investigation of several root designs for cermet turbine blades in turbojet engine III : curved-root design

Pinkel, Benjamin Deutsch, George C Morgan, William C
naca-rm-e55j04
December 28, 1955


Stresses om tje root fastenings of turbine blades were appreciably reduced by redesign of the root. The redesign consisted in curving the root to approximately conform to the camber of the airfoil and elimination of the blade platform. Full-scale jet-engine tests at rated speed using cermet blades of the design confirmed the improvement.

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