Validation and Instrumentation of a Small Modular Multi-Stage Axial Compressor for Ice Crystal Icing Research



International Conference on Icing of Aircraft, Engines, and Structures
Authors Abstract
The National Research Council of Canada (NRC) has undergone the development of a Small Axial Compressor Rig for modelling altitude ice accretion in aircraft engines. The rig consists of two axial compressor stages measuring approximately 150mm in diameter, an extension duct to allow residence time for partial melting of ice crystals and a test piece. The axial compressor stages are intended to provide realistic engine conditioning such as fracture, pressure rise, temperature rise and centrifuging of glaciated ice crystals entering the rig. The rig was designed for use in altitude icing wind tunnels such as the NRC’s altitude icing wind tunnel (AIWT), research altitude test facility (RATFac.), and those of other organization such as NASA Glenn and Technical University of Braunshweig. Previous development work [1] provided partial validation of the aerodynamic performance of just the first compressor stage at 90% power. Recent development work has concluded the aerodynamic validation of both the first and the second stages and performance was found to be satisfactory for purpose. A prediction of the ice accretion behavior of the rig based on validated performance is provided. Details of the instrumentation scheme including measurement technique for the radial distribution of ice crystal downstream of the compressor stages, and measurement of particle sizes before and after each stage are also presented.
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Neuteboom, M., Chalmers, J., and Currie, T., "Validation and Instrumentation of a Small Modular Multi-Stage Axial Compressor for Ice Crystal Icing Research," SAE Technical Paper 2019-01-1940, 2019,
Additional Details
Jun 10, 2019
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Technical Paper