[+] Author and Article Information
Alexander Hergt

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

Sebastian Grund

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

Joachim Klinner

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

Ulrich Siller

Wankelstr. 57 Cologne, 50996 Germany ulrich.siller@aerodesignworks.com

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 22, 2019; published online xx xx, xxxx. Assoc. Editor: Kenneth Hall.

ASME doi:10.1115/1.4043280 History: Received September 11, 2018; Accepted March 22, 2019


The development of axial compressors has already reached a high level. Therefore an enlargement of the design space by means of new or advanced aerodynamic methods is necessary in order to achieve further enhancements. The tandem arrangement of profiles in a transonic compressor blade row is such a method. It is necessary to address the design aspects a bit more in detail in order to efficiently apply this blading concept to turbomachinery. Therefore, in the current study the known design aspects of tandem blading in compressors will be summed up under consideration of the aerodynamic effects and construction characteristics. Based on this knowledge, a new transonic compressor tandem cascade (DLR TTC) with an inflow Mach number of 0.9 is designed using modern numerical methods and a multi objective optimization process. The aim of the ensuing experimental and numerical investigation is to answer the question, whether the tandem cascade resulting from the modern design process fulfils the described design aspects and delivers the requested performance and efficiency criteria. The experiments are performed at the Transonic Cascade Wind Tunnel of DLR in Cologne. The experimental results show an increase in losses and a reduction of the cascade deflection by about 2 degrees at the ADP compared to design concept. Due to the extremely high loading the cascade performance at off-design conditions are not achieved. The reasons for the discrepancies are discussed in the paper. Nevertheless, the experimental and numerical results allow a good understanding of the aerodynamic effects.

Copyright © 2019 by ASME
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