METHOD AND APPARATUS FOR REDUCING ROTOR ASSEMBLY CIRCUMFERENTIAL RIM STRESS

A rotor assembly (10) for a gas turbine engine (12) operates with reduced circumferential rim stress. The rotor assembly includes a rotor (14) including a plurality of rotor blades (26) extending radially outward from an annular rim (20). A root fillet (80) extends circumferentially around each blad...

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Bibliographische Detailangaben
Hauptverfasser:	DECKER, JOHN JARED, MIELKE, MARK JOSEPH
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING COMBINED OPERATIONS ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS OTHER WORKING OF METAL PERFORMING OPERATIONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	A rotor assembly (10) for a gas turbine engine (12) operates with reduced circumferential rim stress. The rotor assembly includes a rotor (14) including a plurality of rotor blades (26) extending radially outward from an annular rim (20). A root fillet (80) extends circumferentially around each blade between the blades and rim. The rim includes an outer surface (28) including a plurality of concave indentations (90) extending between adjacent rotor blades and forming a compound radius. Each indentation extends from a leading edge (40) of the rotor blades towards a trailing edge (42) of the rotor blades.