| Summary: | Ice crystal icing events provide significant challenges to air-breathing propulsion systems. Partial melting of initially glaciated free-stream ice can lead to significant ice build-up on stationary components; these growths may degrade performance or shed and impact downstream stages. There is limited information on the role of wall heat flux in the initiation and stabilisation of accretion, and in subsequent shedding events. Experimental campaigns are often unable to wall heat flux, and have not yet replicated typical engine cycles. Consequently, there is a shortage of reliable boundary conditions for computational simulations. This paper first considers previous studies of heat flux history during icing events, before the presenting the results of a new experimental study conducted using the Ice Crystal Environment – Modular Axial Compressor Rig (ICE-MACR) at the National Research Council of Canada (NRC). High-fidelity wall temperature and heat transfer data are presented for a novel test article typical of an exit outlet guide vane featuring cambered vanes and flow path curvature. Qualitative accretion images are provided with corresponding spatially and temporally resolved wall temperature and heat transfer data. These early findings provide a route to deeper understanding of mechanisms at the wall-ice interface which determine formation and build-up, contributing to improved icing prediction and prevention strategies in aviation.
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