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3D Profile Design and Optimization of a Rotor for a Low Speed Axial Compressor Wind Tunnel
Zitatschlüssel 2019_mihalyovics_dlrk
Autor Mihalyovics, J. and Gambel, J. and Peitsch, D.
Seiten 490163
Jahr 2019
DOI 10.25967/490163
Ort Darmstadt, Germany
Journal Deutscher Luft- und Raumfahrtkongress
Monat 10
Notiz Technische Universität Berlin:
J. Mihalyovics, J. Gambel, D. Peitsch
Herausgeber Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.
Wie herausgegeben Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0)
Zusammenfassung The chair of aero engines at the Technical University of Berlin operates a low speed compressor test rig used for experimental investigations on the influences of a pressure-gain combustion on compressor components. Current interests and major projects focused on the compressor stator. The wind tunnel shall be extended with a rotor to investigate the performance during periodic throttling invoked by pressure-gain combustion. To achieve the conception criteria a rotor was designed and subsequently optimized. This was done in a classic 2D approach utilizing the MISES collection of programs for cascade analysis and design. Amongst others, MISES was used for a systematical parameter study. Subsequently, objective functions were defined to select optimal profiles on each rotor blade design section. The blade design derived from the parameter study was then processed with the ANSYS CFD suite. Within the ANSYS workbench, a response surface based optimization was performed using a limited set of input parameters that define the blade geometry and a set of output parameters that quantify the calculated flow field.
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