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Research Papers

Experimental Investigation on Droplet Behavior in a Transonic Compressor Cascade

[+] Author and Article Information
Niklas Neupert

Mem. ASME
Laboratory of Turbomachinery,
Department of Power Engineering,
Helmut-Schmidt University,
Hamburg 22043, Germany
e-mail: neupert@hsu-hh.de

Birger Ober

Laboratory of Turbomachinery,
Department of Power Engineering,
Helmut-Schmidt University,
Hamburg 22043, Germany

Franz Joos

Professor
Mem. ASME
Laboratory of Turbomachinery,
Department of Power Engineering,
Helmut-Schmidt University,
Hamburg 22043, Germany
e-mail: joos@hsu-hh.de

Modified for clarity in this context.

The characteristic length for the Reynolds number and the Weber number is set to be the boundary layer thickness

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 25, 2014; final manuscript received August 4, 2014; published online October 7, 2014. Editor: Ronald Bunker.

J. Turbomach 137(3), 031009 (Oct 07, 2014) (8 pages) Paper No: TURBO-14-1180; doi: 10.1115/1.4028351 History: Received July 25, 2014; Revised August 04, 2014

In recent years, overspray fogging has become a powerful means for power augmentation of industrial gas turbines (GT). Most of the studies concerning this topic focus on the problem from a thermodynamic point of view. Only a few studies, however, were undertaken to investigate the droplet behavior in the flow channel of a compressor. In this paper, results of experimental investigation of a water laden flow through a transonic compressor cascade are presented. A finely dispersed spray was used in the measurements (D10 < 10 μm). Results of the droplet behavior are shown in terms of shadowgraphy images and images of the blade surface film pattern. The angle of attack, the incoming velocity, and the water load were varied. The qualitative observations are related to laser Doppler and phase Doppler anemometer (LDA/PDA) data taken in the flow channel and at the outlet of the cascade. The data represent a base for numerical and mean line models of two-phase compressor flow.

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References

Figures

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Fig. 2

Definition of cascade flow properties

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Fig. 3

Droplet spectrum of the incoming flow measured at nozzle exit and in the inlet of the cascade

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Fig. 1

Sketch of the test rig

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Fig. 7

Droplet breakup regimes occurring in the acceleration zone at Ma1 = 0.89, ξw = 1.3%, and β1 = 156 deg

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Fig. 8

Wall film pattern at ξw = 1.3%, Ma1 = 0.89 (left), Ma1 = 0.89 (right), β1 = 149 deg (top), and β1 = 153 deg (bottom)

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Fig. 4

Shadowgraphy images showing qualitative droplet behavior at β1 = 149 deg (top) and β1 = 154 deg (bottom); ξw = 1.3% and Ma1 = 0.89

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Fig. 5

Contourplot of D10 (top) and D32 (bottom) around the profile at Ma1 = 0.89, ξw = 1.3%, and β1 = 154 deg

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Fig. 6

Weber numbers for droplet diameters of 40–60 μm (top) and >60 μm (bottom) at Ma1 = 0.89, ξw = 1.3%, and β1 = 154 deg

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Fig. 12

Normalized D32 and D10 at water loads of ξw = 1.3% and ξw = 2.2% at Ma1 = 0.89 at 0.5c behind the trailing edge

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Fig. 13

Normalized D32 and D10 at Ma1 = 0.89 and Ma1 = 0.80 with ξw = 2.1% at 0.5c behind the trailing edge

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Fig. 9

Shock–rivulet interaction at ξw = 1.3%, Ma1 = 0.97, and β1 = 154 deg

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Fig. 10

Pitchwise distribution of the normalized D32 at ξw = 1.3%, Ma1 = 0.89 at 0.5c behind the trailing edge

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Fig. 11

Pitchwise distribution of the normalized D10 at ξw = 1.3%, Ma1 = 0.89 at 0.5c behind the trailing edge

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