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Research Papers

Three-Dimensional Flow Field in Highly Loaded Compressor Cascade

[+] Author and Article Information
Ch. Beselt

Chair for Aero Engines
Department of Aeronautics and Astronautics,
Technische Universität Berlin,
Marchstr. 12-14,
Berlin 10587, Germany
e-mail: Christian.Beselt@ilr.tu-Berlin.de

M. Eck

Chair for Aero Engines
Department of Aeronautics and Astronautics,
Technische Universität Berlin,
Marchstr. 12-14,
Berlin 10587, Germany
e-mail: Mario.Eck@ilr.tu-Berlin.de

D. Peitsch

Professor
Chair for Aero Engines
Department of Aeronautics and Astronautics,
Technische Universität Berlin,
Marchstr. 12-14,
Berlin 10587, Germany
e-mail: Dieter.Peitsch@tu-Berlin.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 7, 2014; final manuscript received July 19, 2014; published online August 8, 2014. Editor: Ronald Bunker.

J. Turbomach 136(10), 101007 (Aug 08, 2014) (10 pages) Paper No: TURBO-14-1114; doi: 10.1115/1.4028083 History: Received July 07, 2014; Revised July 19, 2014

Within the present paper, a detailed experimental investigation is presented. The influence of blade loading on the development and interaction of secondary flow structures within an annular compressor stator cascade (CSC) is examined. Experimental results at 3% chord hub clearance were obtained at four different blade loadings. Included are blade and endwall flow visualization, time resolved measurements of the static pressure on the endwall and radial–circumferential hot-wire traverse measurements within the passage as well as five-hole probe traverse measurements at the inlet and the outlet of the passage. The experimentally obtained results give detailed insight on the effect of the incidence on the development and interaction of the clearance vortex, horseshoe vortex, and the passage vortex. Furthermore, it will be shown that a vortex breakdown of the clearance vortex occurs at higher loadings.

Copyright © 2014 by ASME
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References

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Figures

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Fig. 3

Sensor positions of the Kulite sensor array (filled = sensor)

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Fig. 4

Measurement setup and orientation of the single hot-wire sensor

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Fig. 5

Inlet and outlet conditions: circumferential-mass averaged Ma1 and Ma2, inflow angle β1 and flow turning Δβ

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Fig. 6

Total pressure loss cpt at the exit plane of the CSC

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Fig. 7

Surface flow visualization at the hub for low loads

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Fig. 8

Surface flow visualization at the hub for high loads

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Fig. 9

Distribution of mean static pressure coefficient and STD

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Fig. 10

Contour plots of normalized velocity |u¯| = u¯/umax,Ax.m;m = 1...8

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Fig. 11

Contour plots of normalized STD |STD| = STD/umax,Ax.m;m = 1...8

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Fig. 12

Evolution of the shear layer instability between clearance vortex and main flow; topology of the momentum exchange

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Fig. 13

Interpretation of the skewness in vortex flows in the presence of a shear layer instability

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Fig. 14

Separation on FP [1]; transfer to current investigation iM = 4 deg

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Fig. 15

Isosurface of Sk = 0.75 and distribution of the normalized STD between |STD|=0.1-0.2 at Ax = 8, 6, 4, 2, and 1 (iM = 0 deg (a), iM = 4 deg (b), iM = 7.9 deg (c), and iM = 9.8 deg (d))

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Fig. 16

Schematic drawing of the secondary flow structures an an incidence angle of iM = 0 deg

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Fig. 17

Schematic drawing of the flow separation and the clearance vortex breakdown due to high loading at an incidence angle of iM = 9.8 deg

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