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F. Bakhtiari, F. Wartzek, S. Leichtfuß, H.-P. Schiffer, G. Goinis, E. Nicke
The Institute of Gas Turbines and Aerospace Propulsion at the Technische Universität Darmstadt operates a transonic compressor test rig that represents the typical front-stage of a turbofan high-pressure compressor. The baseline stator was designed in the 1990s and the geometry no longer conforms to modern turbo machine designs and trends in premature flow separation. This paper presents the modification of the current baseline stator design and the development of a new 3D stator using an automated multi-objective optimization process with more than 70 free design variables, two objective functions and 3D CFD for different operating points. The result of the optimization was a new stator design with distinct 3D features, which shows no signs of flow separation across the whole operation range and homogenous angular distribution of outflow. The isentropic efficiency could thus be increased by a maximum of 2.5% while maintaining the same range of operability. As part of this process, the geometric parameters with the most significant impact on aerodynamic behaviour are identified. Therefore, the focus is on the aerodynamic influence of 3D features such as bow and sweep, which primarily reduce total pressure loss. The presented research work was done in a joint collaboration between DLR Institute of Propulsion Technology and Technische Universität Darmstadt (GLR).
Deutscher Luft- und Raumfahrtkongress 2015, Rostock
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2015
21,0 x 29,7 cm, 10 Seiten
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