Method and apparatus for reducing rotor assembly...

Details Method and apparatus for reducing rotor assembly... Method and apparatus for reducing rotor assembly...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/02 (2006.01) F01D 5/14 (2006.01)

Patent

CA 2354834

A rotor assembly (14) for a gas turbine engine (10) operates with reduced circumferential rim stress. The rotor assembly includes a rotor (16) including a plurality of rotor blades (18) and a radially outer platform (48). The rotor blades extend radially outward from the platform. A root fillet (80) extends circumferentially around each blade between the blades and platforms. The platforms include an outer surface (50) including a plurality of indentations (64) extending between adjacent rotor blades. Each indentation extends from a leading edge (60) of the platform to a trailing edge (62) of the platform with a depth (72) that tapers to an approximate zero depth at the trailing edge.

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