Impact of Engine Icing on Jet Engine Compressor Flow Dynamics Reema Kundu * and J.V.R. Prasad † School of Aerospace Engineering Georgia Institute of Technology Atlanta, GA 30332-0150 Andy Breeze-Stringfellow Peter Szucs Tsuguji Nakano GE Aviation Cincinnati, OH 45215 The effort develops a computational methodology for evaluating the performance of a compressor to atmospheric ice ingestion. A fundamental understanding of the transient compressor response to the presence of discrete ice crystals, water droplets and vapor, requires study of the coupled interaction between the continuous (air) phase and the dis- crete (ice crystals and water droplets) phase in the compressor. A thermodynamic model is constructed to simulate icing physics associated with heat and mass transfer with the surrounding airflow. A Lagrangian approach is used to track the discrete phase through the compressor. Source terms imparted by phase changes of the ice crystals and water droplets are introduced in the governing equations of the continuous phase. The impact of icing conditions is inferred from the numerical analysis of the compressor flow field. Two- way and one-way coupling between the icing model and compressor flow model has been implemented and compared. Finally the dynamic response of the compressor to ingested ice crystals is investigated. Nomenclature ˙ m mass flow rate ˙ w s shaft power per unit volume T temperature h fg latent heat of evaporation h m mass transfer coefficient k thermal conductivity Pr Prandtl number Sc Schmidt number φ flow coefficient, u/U ψ f body force coefficient ρ density A flow-path area C P specific heat capacity e 0 total internal energy f body force per unit volume H Total enthalpy h Heat transfer coefficient L axial length of a blade row m p mass of single ice crystal or water droplet n number of ice crystals and water droplets N rpm p pressure q Specific humidity r m pitch-line radius S energy energy source term from the discrete phase S mass mass source term from the discrete phase S mom momentum source term from the discrete phase U pitch-line blade rotational speed, ωr u axial component of flow velocity v θ circumferential component of flow velocity Subscripts θ circumferential component x axial component bld bleed p particle: water droplets and ice crystals wv water vapor * Graduate Research Assistant, AIAA Student Member † Professor, AIAA Fellow. 1 of 12 American Institute of Aeronautics and Astronautics