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Experiments in Fluids

, 60:96 | Cite as

Experimental investigation of shock-induced separation and flow control in a transonic compressor cascade

  • Joachim KlinnerEmail author
  • Alexander Hergt
  • Sebastian Grund
  • Christian E. Willert
Research Article

Abstract

 The influence of transition control on shock-induced flow separation was investigated in a highly loaded transonic compressor cascade at an inlet Mach number of 1.21 and a chord-based Reynolds number of \(1.4 \times 10^6\). Transition was influenced by raising the free-stream turbulence from 0.5 to 2.5%. Two further cases employed either air-jet vortex generators (AJVG) or a surface roughness patch as transition control devices. Velocity fields in the vicinity of the unsteady transonic separation were captured by particle image velocimetry (PIV). Blade flexure induced by the unsteady aerodynamic loading was tracked for each image and compensated individually prior to PIV processing. The captured flow fields indicate shape variations of the separation region, while the shock foot moves within a range of up to 20% of chord. The frequency of separation for each investigated case was assessed on the number of vectors with negative velocity in each PIV sample. To further quantify the size of the separation region, the statistically independent PIV samples were conditionally averaged for various passage shock positions at a resolution of 1% chord length. Insight to the dynamics and frequency of the passage shock motion was further provided by high-speed shadowgraphy. Large bubble separation occurs if the turbulence of the incoming flow is low. The size of separation region decreases when AJVGs are applied but still exhibits bubble separation as the passage shock moves downstream. The size of the separation region is significantly reduced either if a roughness patch is applied or if the turbulence level of the incoming flow is high. The flow conditions showing bubble separation in the mean flow also exhibit distinct spectral peaks indicating periodic shock oscillations.

Graphical abstract

Notes

Acknowledgements

Part of the work presented herein is supported by the EU research project TFAST (Transition Location Effect on Shock Wave Boundary Layer Interaction, project no. 265455) of the 7th Framework Programme whose support is gratefully acknowledged. We thank our reviewers for their constructive remarks and detailed discussion on the content of the earlier version of the manuscript.

Supplementary material

348_2019_2736_MOESM1_ESM.mp4 (519 kb)
Supplementary material 1 (mp4 519 KB)
348_2019_2736_MOESM2_ESM.mp4 (614 kb)
Supplementary material 2 (mp4 613 KB)

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Copyright information

© Springer-Verlag GmbH Germany, part of Springer Nature 2019

Authors and Affiliations

  1. 1.Institute of Propulsion Technology, Measurement Technology, Linder HoeheGerman Aerospace Center (DLR)CologneGermany
  2. 2.Institute of Propulsion Technology, Fan and Compressor, Linder HoeheGerman Aerospace Center (DLR)CologneGermany

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