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Preliminary Investigation of Several Root Designs for Cermet Turbine Blades in Turbojet Engine III : Curved-root DesignStresses 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.
Document ID
19930088975
Document Type
Other
Authors
Pinkel, Benjamin
Deutsch, George C
Morgan, William C
Date Acquired
August 16, 2013
Publication Date
December 28, 1955
Report/Patent Number
NACA-RM-E55J04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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