Control of Flow Separation in Adverse Pressure Gradients by Means of Crosswise Grooved Surfaces for Turbo Machine Applications

  • W. Hage
  • R. Meyer
  • C.O. Paschereit
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 96)


The total pressure losses in a compressor stage are strongly affected by sec-ondary flow effects such as corner separation. Experiments in a highly loaded com-pressor cascade were performed to minimize the losses using a grooved surface on the side walls under cross flow conditions. This geometry hampers the secondary flow in the cascade in such a way, that the corner separation is less pronounced. The total pressure losses are reduced by 9.8% and the flow turning angle is increased. The experiments were accomplished at Reynolds numbers up to Re = 0 56 · 10 (based on 40 mm chord of the vane profile) and Mach numbers up to M = 0.67. To understand the flow physics of the crosswise grooves, additional experiments at lower Reynolds numbers were performed.


Adverse Pressure Gradient Pressure Recovery Total Pressure Loss Compressor Cascade Groove Structure 
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Copyright information

© Springer-Verlag Berlin Heidelberg 2007

Authors and Affiliations

  • W. Hage
  • R. Meyer
    • 1
  • C.O. Paschereit
    • 2
  1. 1.Institute of Propulsion Technology, Dept. of Engine AcousticsDLR (German Aerospace Center)BerlinGermany
  2. 2.Institute of Fluid Mechanics and Engineering AcousticsTechnical University of BerlinBerlinGermany

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