Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part 1—Quasi-Steady Flow Field and Comparison With Steady-State Data

[+] Author and Article Information
H. D. Schulz, H. E. Gallus, B. Lakshminarayana

Institut für Strahlantriebe und Turboarbeitsmaschinen, RWTH Aachen, D-5100 Aachen, Federal Republic of Germany

J. Turbomach 112(4), 669-678 (Oct 01, 1990) (10 pages) doi:10.1115/1.2927707 History: Received February 14, 1989; Online June 09, 2008


An experimental study of three-dimensional flow field in an annular compressor cascade with an upstream rotor has been carried out at four different incidences to the stator blade. Blade boundary layers and the three-dimensional flow field at the exit are surveyed using a hot-wire sensor and a five-hole probe, respectively. The data on the blade boundary layer, passage flow, and separated corner flow are presented. The upstream rotor wake has a major influence on the transition, laminar separation bubble, extent of wall/corner flow separation, aerodynamic losses, secondary flow, and three-dimensional flow inside the passage. A detailed interpretation of the effects of upstream wakes on the entire passage flow is presented and compared with the data in the absence of a rotor.

Copyright © 1990 by The American Society of Mechanical Engineers
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