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Research Papers

Turbine Stator Well CFD Studies: Effects of Coolant Supply Geometry on Cavity Sealing Performance

[+] Author and Article Information
Antonio Andreini, Bruno Facchini

Department of Energy Engineering “S. Stecco,” University of Florence, Via S. Marta 3, Florence 50139, Italy

Riccardo Da Soghe1

Department of Energy Engineering “S. Stecco,” University of Florence, Via S. Marta 3, Florence 50139, Italyriccardo.dasoghe@htc.de.unifi.it

1

Corresponding author.

J. Turbomach 133(2), 021008 (Oct 21, 2010) (11 pages) doi:10.1115/1.4000570 History: Received July 20, 2009; Revised July 27, 2009; Published October 21, 2010; Online October 21, 2010

The increase of aeroengine performance through the improvement of aerodynamic efficiency of core flow is becoming more and more difficult to achieve. However, there are still some devices that could be improved to enhance global engine efficiency. Particularly, investigations on the internal air cooling systems may lead to a reduction of cooling air with a direct benefit to the overall performance. At the same time, further investigations on heat transfer mechanisms within turbine cavities may help to optimize cooling air flows, saving engine life duration. This paper presents a computational fluid dynamics (CFD) study aimed at the characterization of the effects of different geometries for cooling air supply within turbine cavities on wall thermal effectiveness and sealing mass flow rate. Several sealing air supply geometries were considered in order to point out the role of cooling air injection position, swirl number, and jet penetration on the cavities’ sealing performance. Steady state calculations were performed using two different computational domains: the first consists of a sector model of the whole turbine including the second stator well, while the second is a cut-down model of the stator well. Thanks to the simplified geometry of the test rig with respect to actual engines, the study has pointed out clear design suggestions regarding the effects of geometry modification of cooling air supply systems.

Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Reduced mass flow through the interstage seal and flow Sn at the seal inlet

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Figure 2

Analyzed geometry

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Figure 3

Sector model mixing planes position

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Figure 4

Cut-down model domain

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Figure 7

90 g/s via drive arm holes

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Figure 8

70 g/s via drive arm holes

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Figure 9

50 g/s via drive arm holes

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Figure 10

Axial angling: coolant streamlines

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Figure 11

Axial angling: cavity wall’s thermal effectiveness

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Figure 12

Tangential angling: coolant streamlines

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Figure 13

Tangential angling: cavity wall’s thermal effectiveness

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Figure 14

Coupling effects: coolant streamlines

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Figure 15

Coupling effects: cavity wall’s thermal effectiveness

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Figure 16

Cut-down model reliability: cavity wall’s thermal effectiveness

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Figure 17

Qualitative pressure contour plot near the hub of the second rotor row

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Figure 18

Axial position: coolant streamlines

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Figure 19

Axial position: cavity wall’s thermal effectiveness

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Figure 20

Holes angling: coolant streamlines

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Figure 21

Holes angling (normalized vector plot): left original design and right axial angled design

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Figure 22

Holes angling: cavity wall’s thermal effectiveness

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Figure 23

Axial position: coolant streamlines

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Figure 24

Axial position: cavity wall’s thermal effectiveness

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