This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Ice Particle Analysis of the Honeywell ALF502 Engine Booster
Technical Paper
2015-01-2131
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
A flow and ice particle trajectory analysis was performed for the booster of the Honeywell ALF502 engine. The analysis focused on two closely related conditions one of which produced an icing event and another which did not during testing of the ALF502 engine in the Propulsion Systems Lab (PSL) at NASA Glenn Research Center. The flow analysis was generated using the NASA Glenn GlennHT flow solver and the particle analysis was generated using the NASA Glenn LEWICE3D v3.63 ice accretion software. The inflow conditions for the two conditions were similar with the main differences being that the condition that produced the icing event was 6.8 K colder than the non-icing event case and the inflow ice water content (IWC) for the non-icing event case was 50% less than for the icing event case. The particle analysis, which considered sublimation, evaporation and phase change, was generated for a 5 micron ice particle with a sticky impact model and for a 24 micron median volume diameter (MVD), 7 bin ice particle distribution with a supercooled large droplet (SLD) splash model used to simulate ice particle breakup. The particle analysis did not consider the effect of the runback and re-impingement of water resulting from the heated spinner and anti-icing system. The results from the analysis showed that the amount of impingement for the components were similar for the same particle size and impact model for the icing and non-icing event conditions. This was attributed to the similar aerodynamic conditions in the booster for the two cases. The particle temperature and melt fraction were higher at the same location and particle size for the non-icing event than for the icing event case due to the higher incoming inflow temperature for the non-event case. The 5 micron ice particle case produced higher impact temperatures and higher melt fractions on the components downstream of the fan than the 24 micron MVD case because the average particle size generated by the particle breakup was larger than 5 microns which yielded less warming and melting. The analysis also showed that the melt fraction and wet bulb temperature icing criterion developed during tests in the Research Altitude Test Facility (RATFac) at the National Research Council (NRC) of Canada were useful in predicting icing events in the ALF502 engine. The development of an ice particle impact model which includes the effects of particle breakup, phase change, and surface state is necessary to further improve the prediction of ice particle transport with phase change through turbomachinery.
Citation
Bidwell, C. and Rigby, D., "Ice Particle Analysis of the Honeywell ALF502 Engine Booster," SAE Technical Paper 2015-01-2131, 2015, https://doi.org/10.4271/2015-01-2131.Also In
References
- Mason , J ; Strapp , W and Chow , P The Ice Particle Threat to Engines in Flight 44th AIAA Aerospace Sciences Meeting 4 2006 2445 2465
- Mazzawy , R. and Strapp , J. Appendix D - An Interim Icing Envelope SAE Technical Paper 2007-01-3311 2007 10.4271/2007-01-3311
- Oliver , M. Validation Ice Crystal Icing Engine Test in the Propulsion Systems Laboratory at NASA Glenn Research Center AIAA 2014-2898 2014
- Steinthorsson , E. , Liou , M. , and Povinelli , L. Development of an Explicit Multiblock/Multigrid Flow Solver for Viscous Flows in Complex Geometries AIAA-93-2380 (NASATM-106356) 1993
- Bidwell , C. , Potapczuk , M. Users Manual for the NASA Lewis Three-Dimensional Ice Accretion Code (LEWICE3D) NASATM-105974 December 1993
- Program Development Corporation GridPro GUI Manual Version 1.0 September 24 2014
- Bidwell , C. A Lagrangian Parcel Based Mixing Plane Method for Calculating Water Based Mixed Phase Particle Flows in Turbo-machinery 10.1007/s40571-015-0033-z Journal of Computational Particle Mechanics February 2015
- Rigby , D. , Bidwell , C. Three Dimensional Simulation of Flow in an Axial Low Pressure Compressor at Engine Icing Operating Points SAE Technical Paper 2015-01-2132 2015 10.4271/2015-01-2132
- Tsao , J. , Struk , P. , Oliver , M. Possible Mechanisms for Turbofan Engine Crystal Icing at High Altitude AIAA 2014-3044 2014
- Jorgenson , P. , Veres , J. Modeling Commercial Turbofan Engine Icing Risk With Ice Crystal Ingestion AIAA 2013-2679 2013
- Wright , W. , Jorgenson , P. , Veres , J. Mixed Phase Modeling in GlennICE with Application to Engine Icing AIAA 2010-7674 2010
- Currie , T. , Fuleki , D. , Mahallati , A. Experimental Studies of Mixed-Phase Sticking Efficiency for Ice Crystal Accretion in Jet Engines AIAA 2014-3049 2014