Simulation of Ice Particle Breakup and Ingestion into the
Honeywell Uncertified Research Engine (HURE) 2019-01-1965
Numerical solutions have been generated which simulate flow inside an aircraft engine flying at altitude through an ice crystal cloud. The geometry corresponds to the Honeywell Uncertified Research Engine (HURE) which was recently tested in the NASA Propulsion Systems Laboratory (PSL). The simulations were carried out at predicted operating points with a potential risk of ice accretion. The extent of the simulation is from upstream of the engine inlet to downstream past the strut in the core and bypass. The flow solution is produced using GlennHT, a NASA inhouse code. A mixing plane approximation is used upstream and downstream of the fan. The use of the mixing plane allows for steady state solutions in the relative frame. The flow solution is then passed on to LEWICE3D for particle trajectory, impact and breakup prediction. The LEWICE3D code also uses a mixing plane approximation at the boundaries upstream and downstream of the fan. A distribution of particle sizes is introduced upstream. Predicted collection efficiency results are presented on various surfaces. The redistribution of particle sizes and mass are also investigated at various axial locations. Predicted particle temperature and melt ratio are also included in the discussion.
David L. Rigby, William Wright, Ashlie Flegel, Michael King
Vantage Partners Limited, NASA Glenn Research Center
International Conference on Icing of Aircraft, Engines, and Structures