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SUMMARY:Harmonic Balance Method applied to vibration of aircraft engine in
  the presence of contact nonlinearities - Dr Loic Salles\, Imperial Colleg
 e
DTSTART:20191108T160000Z
DTEND:20191108T170000Z
UID:TALK131074@talks.cam.ac.uk
CONTACT:46601
DESCRIPTION:High-cycle fatigue caused by large resonance stresses remains 
 one of the most common causes of turbine blade failures.  Harmonic Balance
  Method is an efficient technique to model the nonlinear vibration of turb
 omachinery components. The first part of the presentation will present the
  HBM and the continuation methods. In the second part we will focus on fri
 ction damping. Friction dampers are one of the most effective and practica
 l solutions to limit the vibration amplitudes\, and shift the resonance fr
 equencies of the turbine assemblies far from operating speeds. However\, p
 redicting the effects of underplatform dampers on the dynamics of the blad
 es with good accuracy still represents a major challenge today\, due to th
 e complex nature of the nonlinear forces at the interface\, characterised 
 by transitions between stick\, slip\, and separation conditions. The most 
 common modelling approaches developed recently are based on the explicit F
 E model for the damper\, and on a dense grid of 3D contact elements compri
 sed of Jenkins elements\, or on a single 2D microslip element on each surf
 ace. In this paper\, a combination of the two approaches is proposed. A 3D
  microslip element\, based on a modified Valanis model is proposed and a s
 eries of these elements are used to describe the contact interface.\n\n
LOCATION:JDB Seminar Room\, CUED
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