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Research Papers

Unsteady Simulation of an Axial Compressor Stage With Casing and Blade Passive Treatments

[+] Author and Article Information
Nicolas Gourdain

Computational Fluid Dynamics Team, CERFACS, 42 Avenue Gaspard Coriolis, Toulouse 31057, France

Francis Leboeuf

Laboratoire de Mécanique des Fluides et d’Acoustique, UMR CNRS 5509, University of Lyon, 36 Avenue Guy de Collongue, Ecully 69034, France

J. Turbomach 131(2), 021013 (Jan 29, 2009) (12 pages) doi:10.1115/1.2988156 History: Received December 18, 2007; Revised May 19, 2008; Published January 29, 2009

This paper deals with the numerical simulation of technologies to increase the compressor performances. The objective is to extend the stable operating range of an axial compressor stage using passive control devices located in the tip region. First, the behavior of the tip leakage flow is investigated in the compressor without control. The simulation shows an increase in the interaction between the tip leakage flow and the main flow when the mass flow is reduced, a phenomenon responsible for the development of a large flow blockage region at the rotor leading edge. A separation of the rotor suction side boundary layer is also observed at near stall conditions. Then, two approaches are tested in order to control these flows in the tip region. The first one is a casing treatment with nonaxisymmetric slots. The method showed a good ability to control the tip leakage flow but failed to reduce the boundary layer separation on the suction side. However, an increase in the operability was observed but with a penalty for the efficiency. The second approach is a blade treatment that consists of a longitudinal groove built in the tip of each rotor blade. The simulation pointed out that the device is able to control partially all the critical flows with no penalty for the efficiency. Finally, some recommendations for the design of passive treatments are presented.

Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic view of the compressor rig

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Figure 2

Calculation domain (up) and mesh details at the rotor leading edge (bottom)

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Figure 3

Mass flow evolution at the outlet of the compressor (Φ=0.83)

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Figure 4

Pressure ratio evolution with respect to mass flow

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Figure 5

Time averaged solution of the axial velocity (a) and relative helicity (b) in the rotor at the nominal operating point (Φ=1.03)–h/H=98%

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Figure 6

Model of the tip leakage vortex and comparison with the simulation (helicity flow field at x/C=50%)

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Figure 7

Time averaged solution of the axial velocity (a) and helicity (b) in the rotor at near stall condition and for the reference case (Φ=0.83)–h/H=98%

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Figure 8

Design of the casing treatment and integration with the compressor stage

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Figure 9

Mass flow evolution at the outlet of the compressor with casing treatment (Φ=0.83)

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Figure 10

Pressure ratio evolution with respect to the mass flow

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Figure 11

Time averaged solution of the axial velocity (a) and helicity (b) in the rotor at near stall condition and with a casing treatment (Φ=0.83)–h/H=98%

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Figure 12

Instantaneous solution of the static pressure in an axial slot (meridian view)

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Figure 13

Design of the longitudinal groove inside a rotor blade

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Figure 14

Mass flow evolution at the outlet of the compressor with longitudinal groove (Φ=0.83)

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Figure 15

Pressure ratio evolution with respect to the mass flow

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Figure 16

Time averaged solution of the axial velocity (a) and helicity (b) in the rotor at near stall condition and with longitudinal grooves (Φ=0.83)

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Figure 17

Streamlines in a rotor groove from a time averaged solution of the radial velocity (Φ=0.83)

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Figure 18

Level of turbulent kinetic energy in the tip gap at a near stall point (Φ=0.83)

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Figure 19

Comparison of the control method impact on the mean flow blockage in the rotor

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Figure 20

Comparison of the isentropic efficiency with the different control strategies

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