Session: 31-11 Boundary Layer Dynamics

Paper Number: 153712

Transonic Blade Design: Quo Vadis? 

The flow through transonic compressor cascades exhibits a complex structure due to the presence of shock waves. The presence of these shocks is decisive for the performance and loss behavior of transonic blading for fans and compressors. Over the past 15 years, experimental and numerical fundamental research at DLR Institute of Propulsion technology in the field of transonic fans and compressors blades has focused on the detailed understanding of the fluid mechanical principles behind the effects. This paper will provide an overview of the research activities and answer the question of what the future research topics will be. The three main flow areas that are essential for performance are examined in more detail. These are the leading edge flow, the suction-side flow area in front of the shock and the shock boundary interaction. Based on the experimental and numerical results, various solution approaches are presented and discussed. The shock boundary layer interaction leads to considerable shock oscillation which reduces the operating range and also causes increased losses. A new design approach of the blade suction side can offer a possibility to reduce this effect.  Shock losses are also significantly influenced by the shape of the leading edge and the pre-shock Mach number. Therefore, the leading edge design and the possibilities of a pre-compression blade design are presented in detail and discussed using an example design. At the end of the day, this paper is intended to provide an inspiration for further research and to clarify the possible potential.

Presenting Author: Alexander Hergt German Aerospace Center (DLR)

Presenting Author Biography: I am scientist in the Institute of Propulsion Technology of the German Aerospace Center (DLR) with 20 years of experience in fan and compressor design and testing. I am heading the group for experimental compressor aerodynamics research in the institute and my main research topics are flow control, shock boundary layer interactions, stall protection, axial compressor design and low Reynolds number effects.
I studied aerospace engineering at the Technical University of Dresden received my diploma in 2004. In 2011 I finished my doctoral thesis at the Technical University of Berlin.

Authors:

Alexander Hergt German Aerospace Center (DLR)
Edwin Joseph Munoz Lopez German Aerospace Center (DLR)
Joachim Klinner German Aerospace Center (DLR)
Anisha Singhatwadia German Aerospace Center (DLR)
Sebastian Grund German Aerospace Center (DLR)