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TECHNICAL PAPERS

Flow Interaction From the Exit Cavity of an Axial Turbine Blade Row Labyrinth Seal

[+] Author and Article Information
A. Pfau, M. Treiber, M. Sell, G. Gyarmathy

Turbomachinery Laboratory, Institute of Energy Technology, Swiss Federal Institute of Technology, 8092 Zurich, Switzerland

J. Turbomach 123(2), 342-352 (Feb 01, 2000) (11 pages) doi:10.1115/1.1368124 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Figures

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Blade form and dimensions (hub)
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Test cascade geometry and measurement position
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h-s-diagram of blade labyrinth system
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Inlet cavity wall pressure distribution (Cp), Δcontour=0.1. The dash lines represent the location of the shroud leading edge.
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Relative pressure distribution within the seal gap
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Total pressure loss (ΔCp0) downstream of the trailing edge (a) 1/12, (b) 1/6, (c) 1/3 axial chord, Δcontour=0.1
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Total pressure loss (ΔCp0) downstream of the trailing edge (a) 1/2, (b) 1 axial chord, Δcontour=0.05
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Velocity components 1/12 axial chord downstream of the trailing edge normalized with c0: (a) axial velocity, (b) circumferential velocity, Δcontour=0.01
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Velocity components 1/6 axial chord downstream of the trailing edge normalized with c0: (a) axial velocity, Δcontour=0.05, (b) radial velocity, Δcontour=0.02
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Wall static pressure measurements (Cp), left on the cavity groove bottom (H=124 percent), right on the channel casing wall (H=100 percent), Δcontour=0.01. Note that the length scale is axially stretched by a factor of 2.
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Secondary flow vectors normalized with c0, 1/2 axial chord downstream of the trailing edge
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Secondary flow vectors normalized with c0, 1 axial chord downstream of the trailing edge
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Sketch of driving mechanisms
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Sketch of flow effects (top view), velocity triangles at Xe≈0.4
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Sketch of flow effects (side view)
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Streamlines of preliminary CFD calculations: viewed from above into labyrinth cavities

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