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) B23P 15/00 (2006.01) F01D 5/06 (2006.01) F01D 5/14 (2006.01) F01D 5/34 (2006.01)

Patent

CA 2358673

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.

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