The patent relates to a transition of improved design for joining the merging surfaces of the airfoil and platform of an axial-flow compressor blade of the cantilevered type. The transition as viewed in profile is a line comprising an essentially straight major portion diverging outwardly from and faired into the airfoil and an outwardly concave minor portion extending along and faired into the platform.
Blade Transition for Axial-Flow Compressors and the Like
1972
7 pages
Report
No indication
English
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