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Research Papers

Time Resolved Experimental Investigations of an Axial Compressor With Casing Treatment

[+] Author and Article Information
R. Emmrich, H. Hönen

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen University, Templergraben 55, D-52062 Aachen, Germany

R. Niehuis1

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen University, Templergraben 55, D-52062 Aachen, Germany

1

Present address: University of the Federal Armed Forces, Munich—Werner-Heisenberg-Weg 39, D-85577 Neubiberg, Germany.

J. Turbomach 131(1), 011018 (Nov 10, 2008) (9 pages) doi:10.1115/1.2813005 History: Received June 22, 2007; Revised August 18, 2007; Published November 10, 2008

A casing treatment with axial and radial skewed slots ending in a plenum chamber has experimentally been investigated at a highly subsonic axial compressor stage. The aim was to investigate the physical phenomenon of this treatment family that is responsible for the stabilization of the blade passage flow and the drop in efficiency mostly observed. The experimentally gained performance results of this configuration showed an extension of the operating range by approximately 50%, while the efficiency for design conditions is reduced by 1.4%. Apart from this, operating points at part load conditions have been observed nearly without any loss in efficiency. The detailed flow analysis is performed by means of results from a 3D pneumatic probe with temperature sensor and a dynamic total pressure probe. The focus of the investigations is on the incidence flow to the compressor rotor, the tip clearance vortex flow in combination with the wall stall separation region and the blade stall due to suction side separation. The casing treatment configuration is investigated with a special interest in detecting those effects which have an impact on the stability and the compressor overall efficiency, including the interaction of the rotor and the stator flow fields.

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Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

Compressor test rig

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Figure 2

Transient total pressure probe (left) and five-hole pressure probe with temperature sensor (right)

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Figure 4

Unsteady wall pressure at stall event, 25% chord length from the blade leading edge

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Figure 5

Static wall pressure rise over the relative axial blade tip chord length

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Figure 6

Circumferential averaged Absolute flow angle alpha in Plane E1

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Figure 7

Circumferential averaged absolute flow angle alpha in Plane E2

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Figure 8

Circumferential averaged total temperature distribution in Plane E2

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Figure 9

Snapshot of the EA total pressure distribution in the rotor exit Plane E2 at maximum efficiency

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Figure 10

Snapshot of the RMS total pressure distribution in the rotor exit Plane E2 at maximum efficiency

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Figure 11

Snapshot of the EA total pressure distribution in the rotor exit Plane E2 at solid casing stall point

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Figure 12

Snapshot of the RMS total pressure distribution in the rotor exit Plane E2 at solid casing stall point

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Figure 13

Snapshot of the EA and rms total pressure distribution in the rotor exit Plane E2 at casing treatment stall point

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Figure 14

Snapshot of the EA total pressure distribution in the stator exit Plane E3 at solid casing stall point

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