A gas turbine engine rotor assembly

Details A gas turbine engine rotor assembly A gas turbine engine rotor assembly

F - Mech Eng,Light,Heat,Weapons

02

C

170/72

F02C 7/00 (2006.01) F01D 25/04 (2006.01)

Patent

CA 2012243

A gas turbine engine rotor assembly has an inertial damper loosely surrounding a portion of the main rotor shaft. The damper is axially compressed between facing abutment surfaces provided on a nut and bevel gear. The damper has two axially spaced rows of circumferentially spaced slots, with the interrupting web portions of each row being circumferentially staggered with respect to one another. The damper is configured and dimensioned so that the axial force exerted by the damper on the nut and bevel gear, the polar moment of inertia of the damper, and the coefficient of friction between the damper end faces and the abutment surfaces, cooperate to effectively damp the excitation of the fifth-stage blades in response to application of a source of vibrations at a particular frequency to the bevel gear.

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