Abstract
In this study, a 3D design procedure for axial flow tandem stage is developed, and then a highly loaded stage is designed with this method. Designed stage is numerically investigated with a CFD code and the stage characteristic map is reported. In order to investigate the effect of highly loaded design, a conventionally loaded compressor stage is designed with single blade for rotor and stator rows. For a better comparison, Chord lengths and hub/shroud geometries are selected same between highly and conventionally loaded compressors. Characteristic map of the conventional compressor is reported too and performance of highly loaded and conventionally loaded compressors are compared. To validate the CFD method, another compressor stage is presented that its geometry and experimental results are available. Performance of the recent compressor stage is numerically investigated and compared with experimental results.
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