Validation of a Small Modular Multi-Stage Axial Compressor for Ice Crystal Icing Research 2019-01-1940
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, The Research Altitude Facility and those of other organization such as NASA Glenn and Braunshwieg University. Previous development work (1.) provided partial validation of the aerodynamic performance of the first compressor stage at 90% power. Recent development work has completed the aerodynamic validation of both the first and the second stages separately as well as verification of the performance of the two combined stages at the full operating conditions. The measured aerodynamic performance has been used to validate numeric CFD code which is used as the foundation for ice accretion prediction codes. Prediction of the ice accretion behavior of the rig is also presented. Details of the instrumentation scheme including measurement technic for the radial distribution of ice crystal downstream of the compressor stages, measurement of particle sizes before and after each stage is also presented.
Martin Neuteboom, Jennifer Chalmers, Thomas Currie
National Research Council Canada
International Conference on Icing of Aircraft, Engines, and Structures