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TECHNICAL PAPERS

The Importance of Shroud Leakage Modeling in Multistage Turbine Flow Calculations

[+] Author and Article Information
Budimir Rosic

Whittle Laboratory, Cambridge University, Cambridge CB3 0DY, UKbr241@eng.cam.ac.uk

John D. Denton, Graham Pullan

Whittle Laboratory, Cambridge University, Cambridge CB3 0DY, UK

J. Turbomach 128(4), 699-707 (Sep 06, 2005) (9 pages) doi:10.1115/1.2181999 History: Received August 30, 2005; Revised September 06, 2005

Three-dimensional steady multistage calculations, using the mixing plane approach, are compared with experimental measurement in a low-speed three-stage model turbine. The comparisons are made with two levels of shroud seal clearance, one representative of a real turbine and one with minimal seal clearance and almost no shroud leakage. Three different calculations are compared. The first computes the main blade path with no modeling of shroud leakage. The second includes a simple model of shroud leakage using sources and sinks on the end-walls, and the third is a multiblock calculation with all leakage paths and cavities computed. It is found that neglect of shroud leakage makes the computed velocity profiles and loss distributions significantly different to those measured. Simple modeling of shroud leakage gives some improvement but full calculation of the leakage flows and cavities is necessary to obtain good agreement between calculation and measurement.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic of model turbine.

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Figure 2

“Zero-leakage” shroud sealing arrangement

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Figure 3

Shroud sealing arrangement with open cavities

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Figure 4

Multip computational grid

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Figure 5

Schematic description of shroud leakage model

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Figure 6

Tblock computational domain (Configuration 2)

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Figure 7

Tblock-stator grid structure

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Figure 8

Cpo contours downstream of the first stator

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Figure 9

Flow visualization and predicted streamlines on the suction side of Stator 1

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Figure 10

Cpo contours-Stator 3 (Configuration 1)

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Figure 11

Measured and predicted pitch-wise averaged yaw angle (Configuration 1)

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Figure 12

Measured and predicted pitch-wise averaged axial velocity (Configuration 1)

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Figure 13

Measured and predicted pitch-wise averaged relative yaw angle (Configuration 1)

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Figure 14

Cpo contours-Stator 3 (Configuration 2)

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Figure 15

Measured and predicted pitch-wise averaged yaw angle (Configuration 2)

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Figure 16

Measured and predicted pitch-wise averaged axial velocity (Configuration 2)

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Figure 17

Measured and predicted pitch-wise averaged relative yaw angle (Configuration 2)

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Figure 18

Radial velocity distribution in the shroud exit cavity

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