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 the numerical results to acceleration and deceleration rates. The results, obtained with and without abradable coating, underline the fundamental nonlinear nature of the analyzed system. It is found that the lower acceleration rates favor the arisal of interaction phenomena, and that the amplitudes of vibration at a given angular speed are generally lower when the blade decelerates.
Full Three-Dimensional Rotor/Stator Interaction Simulations in Aircraft Engines With Time-Dependent Angular Speed
Département de Génie Mécanique,
École Polytechnique de Montréal,
Montréal, QC H3C 3A7, Canada
Department of Mechanical Engineering,
Montréal, QC H3A 0C3, Canada
Vice President for Academics Affairs,
University of Illinois at Urbana-Champaign,
Urbana, IL 61801
Contributed by the Aircraft Engine Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 14, 2016; final manuscript received July 14, 2016; published online October 11, 2016. Editor: David Wisler.
Batailly, A., Legrand, M., and Pierre, C. (October 11, 2016). "Full Three-Dimensional Rotor/Stator Interaction Simulations in Aircraft Engines With Time-Dependent Angular Speed." ASME. J. Eng. Gas Turbines Power. March 2017; 139(3): 031202. https://doi.org/10.1115/1.4034503
Download citation file: