Numerical Investigation of a Transonic Axial Compressor Stage with Inlet Distortions

Jens Iseler (), Andreas Lesser () and Reinhard Niehuis ()
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Jens Iseler: Universität der Bundeswehr München
Andreas Lesser: Universität der Bundeswehr München
Reinhard Niehuis: Universität der Bundeswehr München

A chapter in High Performance Computing in Science and Engineering, Garching/Munich 2009, 2010, pp 185-195 from Springer

Abstract: Abstract This paper refers to a numerical study of a transonic compressor stage investigated for homogenous and disturbed inflow conditions. The simulations were conducted with a Navier-Stokes solver developed by the DLR Cologne. In the first part of the investigations, the flow behavior of the transonic compressor stage was predicted for undisturbed inflow conditions. For those simulations, periodicity was assumed and therefore only one blade passage was considered. The simulations were performed for several operating points at 100% and 85% rotational speed. The numerical results were compared to the experimental data from Dunker and revealed a satisfying agreement concerning the flow behavior. In the second part, steady and unsteady flow simulations for distorted inflow conditions were performed. Here, simulations of the entire compressor stage had to be done and continued.

Keywords: Compressor Stage; Blade Passage; ASME Paper; Stator Blade; Mach Number Distribution (search for similar items in EconPapers)
Date: 2010
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-642-13872-0_16

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DOI: 10.1007/978-3-642-13872-0_16

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