TY - GEN
T1 - Full 3d rotor/stator interaction simulations in aircraft engines with time-dependent angular speed
AU - Batailly, Alain
AU - Legrand, Mathias
AU - Pierre, Christophe
N1 - Publisher Copyright: © Copyright 2016 by ASME.
PY - 2016
Y1 - 2016
N2 - Modern aircraft engine designs feature reduced clearances that may initiate structural contacts between rotating and static components. A numerical strategy dedicated to the simulation of such interactions is here enriched in order to account for time-dependent angular speeds. This contribution first details the evolution of the numerical strategy before validating the developments by comparing numerical results with experimental observations made on an industrial test bench. Further numerical investigations allow to assess the sensitivity of numerical results to acceleration and deceleration rates. Results, obtained with and without abradable coating, underline the fundamental nonlinear nature of the analysed system. It is found that lower acceleration rates favour the arisal of interaction phenomena and that amplitudes of vibration at a given angular speed are generally lower when the blade decelerates.
AB - Modern aircraft engine designs feature reduced clearances that may initiate structural contacts between rotating and static components. A numerical strategy dedicated to the simulation of such interactions is here enriched in order to account for time-dependent angular speeds. This contribution first details the evolution of the numerical strategy before validating the developments by comparing numerical results with experimental observations made on an industrial test bench. Further numerical investigations allow to assess the sensitivity of numerical results to acceleration and deceleration rates. Results, obtained with and without abradable coating, underline the fundamental nonlinear nature of the analysed system. It is found that lower acceleration rates favour the arisal of interaction phenomena and that amplitudes of vibration at a given angular speed are generally lower when the blade decelerates.
UR - https://www.scopus.com/pages/publications/84991677860
UR - https://www.scopus.com/pages/publications/84991677860#tab=citedBy
U2 - 10.1115/GT2016-56715
DO - 10.1115/GT2016-56715
M3 - Conference contribution
T3 - Proceedings of the ASME Turbo Expo
BT - Structures and Dynamics
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016
Y2 - 13 June 2016 through 17 June 2016
ER -