Research Papers

Active Flow Control Concepts on a Highly Loaded Subsonic Compressor Cascade: Résumé of Experimental and Numerical Results

[+] Author and Article Information
Christoph Gmelin

Vincent Zander, Martin Hecklau, Frank Thiele, Wolfgang Nitsche

 Technische Universität Berlin, Straße des 17. Juni 135, 10623 Berlin, Germany

André Huppertz, Marius Swoboda

 Rolls-Royce Deutschland Ltd. & Co. KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany

For more information, see http://ntrs.nasa.gov

J. Turbomach 134(6), 061021 (Sep 04, 2012) (9 pages) doi:10.1115/1.4006308 History: Received July 11, 2011; Revised July 29, 2011; Published September 04, 2012; Online September 04, 2012

This paper presents experimental and numerical results for a highly loaded, low speed, linear compressor cascade with active flow control. Three active flow control concepts employing steady jets, pulsed jets, and zero mass flow jets (synthetic jets) are investigated at two different forcing locations: at the end walls and the blade suction side. Investigations are performed at the design incidence for jet-to-inlet velocity ratios of approximately 0.7 to 3.0 and two different Reynolds numbers. Detailed flow field data are collected using a five-hole pressure probe, pressure tabs on the blade surfaces, and time-resolved particle image velocimetry. Unsteady Reynolds-Averaged Navier-Stokes simulations are performed for a wide range of flow control parameters. The experimental and numerical results are used to understand the interaction between the jet and the passage flow. Variation of jet amplitude, forcing frequency and blowing angle of the different control concepts at both locations allows determination of beneficial control parameters and offers a comparison between similar control approaches. This paper combines the advantages of an expensive yet reliable experiment and a fast but limited numerical simulation. Excellent agreement in control effectiveness is found between experiment and simulation.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 10

Total pressure loss for synthetic jets

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Figure 11

Efficiency of synthetic jets

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Figure 12

Total pressure loss for the numerical parameter variation

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Figure 13

Pressure rise for the numerical parameter variation

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Figure 14

Numerical efficiency of different control concepts and locations

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Figure 15

Secondary flow visualization by isosurfaces of the Q-criteria color coded with the velocity magnitude

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Figure 1

Cascade geometry

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Figure 2

Cascade test section

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Figure 3

Oil flow visualization of the base flow overlaid with numerically calculated wall shear lines on the left and a sketch of the secondary flow pattern on the right

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Figure 4

Pressure coefficient distribution at 0%, 20%, and 40% span for experiment and simulation

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Figure 5

(a) Stator blade with actuator setup, (b) Side wall actuator (cross-section in top-view), (c) Blade actuator (cross-section)

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Figure 6

PIV measurements of the corner vortex at 70% chord of the blade, with iso-lines of the absolute velocity

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Figure 7

Total pressure loss for steady and pulsed jets

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Figure 8

Efficiency of steady and pulsed jets

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Figure 9

Synthetic jet actuator setup



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