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Simulation of Ice Particle Breakup and Ingestion into the Honeywell Uncertified Research Engine (HURE)
Technical Paper
2019-01-1965
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
Numerical solutions have been generated which simulate flow inside an aircraft engine flying at altitude through an ice crystal cloud. The geometry used for this study is the Honeywell Uncertified Research Engine (HURE) which was recently tested in the NASA Propulsion Systems Laboratory (PSL) in January 2018. 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 in-house 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, based on the distribution measured during the test. Predicted collection efficiency and melt ratio results are presented on various surfaces. The redistribution of particle sizes and mass are also investigated at various axial locations and compared to particle measurements in the bypass.
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Rigby, D., Wright, W., Flegel, A., and King, M., "Simulation of Ice Particle Breakup and Ingestion into the Honeywell Uncertified Research Engine (HURE)," SAE Technical Paper 2019-01-1965, 2019, https://doi.org/10.4271/2019-01-1965.Data Sets - Support Documents
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