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Research Papers

Numerical and Experimental Investigations of a Compressor Cascade Flow With Secondary Air Removal

[+] Author and Article Information
Sascha Pönick

e-mail: sascha.poenick@gmx.de

Dragan Kožulović

e-mail: d.kozulovic@tu-braunschweig.de

Rolf Radespiel

Institut für Strömungsmechanik,
Technische Universität Braunschweig,
Bienroder Weg 3,
38106 Braunschweig, Germany

Bernd Becker

e-mail: bernd.becker@rolls-royce.com

Volker Gümmer

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

Only the half of the passage adjacent to the bleed port was refined due to CPU and memory reasons.

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNALOF TURBOMACHINERY. Manuscript received August 22, 2011; final manuscript received September 6, 2011; published online November 8, 2012. Editor: David Wisler.

J. Turbomach 135(2), 021030 (Nov 08, 2012) (10 pages) Paper No: TURBO-11-1190; doi: 10.1115/1.4006570 History: Received August 22, 2011; Revised September 06, 2011

The paper presents numerical and experimental results for a low speed compressor cascade with bleed air removal at the endwall. The aerofoil design is representative for a stator blade in a modern high pressure compressor near the casing wall. Secondary air is commonly supplied by simple bleed geometries downstream of stator rows. The focus of the present investigation was the systematic development of a passage integrated bleed configuration. With the assumption of an invariable bleed mass flow rate it should be designed to provide an advantageous effect on the main flow. Furthermore, a high pressure recovery in the bleed flow was aspired. Steady 3D RANS simulations were performed using the Spalart-Allmaras turbulence model. In both numerical simulations and experiments, an improved performance was found. Beside reduced losses and increased pressure rise, the wake flow downstream of the customized bleed geometry was found to be more homogeneous with decreased deviations due to a favorable influence on the secondary flow.

Copyright © 2013 by ASME
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References

Cumpsty, N. A., 2004, Compressor Aerodynamics, Krieger, Malabar, FL.
Gomes, R. A., Schwarz, C., and Pfitzner, M., 2005, “Aerodynamic Investigations of a Compressor Bleed Air Configuration Typical for Aeroengines,” Proceedings of XVII ISABE, Munich, September 4–9, Paper No. ISABE-2005-1264.
SchwarzC., 2005, “Aerodynamische Untersuchungen an Abblase-Luftsystemen mehrstufiger Axialverdichter,” Ph.D. thesis, Universität der Bundeswehr, München, Germany.
Willis, B. P., Davis, D. O., and Hingst, W. R., 1995, “Flow Coefficient Behaviour for Boundary Layer Bleed Holes and Slots,” Lewis Research Center, OH, NASA Technical Memorandum No. 95-0031.
Leishman, B. A., Cumpsty, N. A., and Denton, J. D., 2007, “Effects of Bleed Rate and Endwall Location on the Aerodynamic Behaviour of a Circular Hole Bleed Off-Take,” ASME J. Turbomach., 129, pp.645–658. [CrossRef]
Leishman, B. A., Cumpsty, N. A., and Denton, J. D., 2007, “Effects of Inlet Ramp Surfaces on the Aerodynamic Behaviour of Bleed Hole and Bleed Slot Off-Take Configurations,” ASME J. Turbomach., 129, pp.659–668. [CrossRef]
Leishman, B. A., and Cumpsty, N. A., 2007, “Mechanism of the Interaction of a Ramped Bleed Slot With the Primary Flow, ASME J. Turbomach., 129, pp.669–678. [CrossRef]
Gümmer, V., Goller, M., and Swoboda, M., 2008, “Numerical Investigations of Endwall Boundary Layer Removal on Highly-Loaded Axial Compressor Blade Rows,” ASME J. Turbomach., 130, pp.115–124. [CrossRef]
Frick, C. W., Davis, W. F., Randall, L. M., and Mossman, E. A., 1945, “An Experimental Investigation of NACA Submerged Duct Entrances,” NACA ACR 5I20, Ames Aeronautical Laboratory, Washington, DC.
NUMECA, 2009, Users Manual Flow Integrated Environment™/Turbo v8.3-1, Brussels, Belgium.
Nerger, D., 2009, “Aktive Strömungsbeeinflussung in ebenen Statorgittern hoher aerodynamischer Belastung durch Ausblasen,” Ph.D. thesis, Technische Universität Braunschweig, Braunschweig, Germany.
Pönick, S., Kožulović, D., Radespiel, R., Becker, B., and Gümmer, V., 2009, “Numerical and Experimental Studies of the Flow Field Details on a Cascade With Endwall Part-Clearance,” ETC2009, Noordwijkerhout, Netherlands, October 4-7.

Figures

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Fig. 1

Bleed port designs and positions

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Fig. 2

Problem of negative bleed for passage integrated bleed offtake

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Fig. 3

Mesh resolution in the bleed port environment

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Fig. 4

Integration planes for the CFD studies

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Fig. 5

Test section of the cascade wind tunnel and geometry data

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Fig. 6

Cross-sectional view of the reference bleed configuration installed

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Fig. 7

Wind tunnel facility with pressure measurement equipment installed

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Fig. 8

Flow topology at both bleed ports near the endwall, RANS

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Fig. 9

Flow topology within the VBP cavity, RANS

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Fig. 10

Flow in the wake plane – measurement

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Fig. 11

Flow in the wake plane – RANS

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Fig. 12

Pitchwise-averaged results for loss coefficient ζV and deviation angle β2

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Fig. 13

Flow visualizations of the blade suction side

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Fig. 14

The wall-near flow topology within the VBP cavity

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Fig. 15

Surface pressure distribution at the blade suction side

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Fig. 16

Pressure distribution along VBP ramp

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Fig. 17

Pressure recovery for both bleed configurations for variable incidence

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Fig. 18

Surface streamlines on VBP ramp for different turbulence models

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Fig. 19

Sensitivities of pressure distribution along VBP ramp

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Fig. 20

Surface streamlines and radial velocity distribution for both bleed configurations for different turbulence models

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