Unsteady Flow Phenomena in Tandem Blade Multi-Stage Axial Compressors

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The very few research research that were conducted on tandem vanes indicates the high potential regarding their various ways of application within turbo compressors and fans. The consequent step to develop essential knowledge and design correlations on tandem blades is to investigate its aerodyamic behavior in a single and multistage environment. In particular, this applies when the turbomachine is operating under unsteady condition. Until now, the time dependent behavior was not assessed in depth. Therefore, the project aims at contributing to the understanding of the time-dependent, three-dimensional flow phenomena under consideration of friction losses within the boundary layers occuring in the environment of rotating machine arrangement.The investigation of the unsteady fluid dynamics is realized on a rotating, multi-stage low-speed compressor rig that is representative for future innovative turbomachinery designs. Focus is set on secondary flow phenomena in regions adjacent to the endwalls and the mutual interactions of the rotor and stator blade rows. Following an holistic approach, this project encompasses both experimental and numerical work. This project is succeeding the former FVV project "aerodynamics of tandem vanes in a compressor cascade" (AIF-Nr. 17454) and delivers complementary results regarding the flow physics of tandem vanes in turbomachinery. This fundamental growth in knowledge results from the intended transition from simplified cascade experiments to investigations in multi-stage turbomachinery environment which allows the derivation of new models for the aerodynamic performance of tandem compressor airfoils.