[+] Author and Article Information
Alexander Hergt

Institute of Propulsion Technology Linder Hoehe Cologne, 51147 Germany alexander.hergt@dlr.de

Joachim Klinner

Institute for Propulsion Technology Linder Hoehe Cologne, 51147 Germany joachim.klinner@dlr.de

Jens Wellner

Linder Hoehe Cologne, 51147 Germany jens.wellner@dlr.de

Chris Willert

Linder Höhe Institute of Propulsion Technology Köln, 51147 Germany chris.willert@dlr.de

Sebastian Grund

Institute of Propolsion Technology Linder Hoehe Cologne, 51147 Germany sebastian.grund@dlr.de

Wolfgang Steinert

Institute of Propulsion Technology Cologne, D-51147 Germany Wolfgang.Steinert@dlr.de

Manfred Beversdorff

Institute of Propulsion Technology Linder Hoehe Cologne, 51147 Germany manfred.beversdorff@dlr.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received September 11, 2018; final manuscript received March 26, 2019; published online xx xx, xxxx. Assoc. Editor: Kenneth Hall.

ASME doi:10.1115/1.4043329 History: Received September 11, 2018; Accepted March 27, 2019


The flow through a transonic compressor cascade shows a very complex structure due to the occurring shock waves. In addition, the interaction of these shock waves with the blade boundary layer inherently leads to a very unsteady flow behaviour. The aim of the current investigation is to quantify this behaviour and its influence on the cascade performance. Therefore, an extensive experimental investigation of a transonic compressor cascade was performed. In this process, the flow phenomena were thoroughly examined for an inflow Mach number of 1.21. The experiments investigate both, the laminar as well as the turbulent shock wave boundary layer interaction within the blade passage and the resulting unsteady behaviour. The experiments show a fluctuation range of the passage shock wave of about 10 percent chord for both cases, which is directly linked with a change of the inflow angle/operating point of the cascade. In addition to the experiments, an unsteady simulation has been carried out in order to capture the unsteady flow behaviour. The results from this simulation show that the fluctuation of the passage shock wave can be reproduced but not in the correct magnitude. Due to this fact, there exist a delta in working range between the shock position where the numerical stall margin is reached and the averaged shock position of experimental cascade stall margin. This is a weak point within the design process of transonic compressor blades, because the working range will not be correct predicted.

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