ROTATING AIRFOIL COMPONENT WITH PLATFORM HAVING A RECESSED SURFACE REGION THEREIN

ROTATING AIRFOIL COMPONENT WITH PLATFORM HAVING A RECESSED SURFACE REGION THEREIN

A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: GIRI SHEO NARAIN, BOMMANAKATTE HARISH, WARD, JR. JOHN DAVID, BANAKAR MOHANKUMAR, LOMAS JONATHAN MATTHEW
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS
INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Beschreibung
Zusammenfassung:A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.