Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Evaluation of Computational Fluid Dynamics and Coupled Fluid-Solid Modeling for a Direct Transfer Preswirl System

[+] Author and Article Information
Umesh Javiya

e-mail: u.javiya@surrey.ac.uk

John Chew

e-mail: j.chew@surrey.ac.uk

Nick Hills

e-mail: n.hills@surrey.ac.uk
Thermo-Fluid Systems UTC,
Faculty of Engineering and Physical Science,
University of Surrey,
Guildford, Surrey,

Klaus Dullenkopf

Institut für Thermische Strömungsmaschinen (ITS),
Karlsruhe Institute of Technology,
76128 Karlsruhe, Germany
e-mail: klaus.dullenkopf@skit.edu

Timothy Scanlon

PO Box 31,
Rolls-Royce Plc, Derby, UK
e-mail: timothy.scanlon@rolls-royce.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Engineering for Gas Turbines and Power. Manuscript received June 24, 2012; final manuscript received August 5, 2012; published online April 18, 2013. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 135(5), 051501 (Apr 18, 2013) (9 pages) Paper No: GTP-12-1214; doi: 10.1115/1.4007752 History: Received June 24, 2012; Revised August 05, 2012

The prediction of the preswirl cooling air delivery and disk metal temperature are important for the cooling system performance and the rotor disk thermal stresses and life assessment. In this paper, standalone 3D steady and unsteady computation fluid dynamics (CFD), and coupled FE-CFD calculations are presented for prediction of these temperatures. CFD results are compared with previous measurements from a direct transfer preswirl test rig. The predicted cooling air temperatures agree well with the measurement, but the nozzle discharge coefficients are under predicted. Results from the coupled FE-CFD analyses are compared directly with thermocouple temperature measurements and with heat transfer coefficients on the rotor disk previously obtained from a rotor disk heat conduction solution. Considering the modeling limitations, the coupled approach predicted the solid metal temperatures well. Heat transfer coefficients on the rotor disk from CFD show some effect of the temperature variations on the heat transfer coefficients. Reasonable agreement is obtained with values deduced from the previous heat conduction solution.

Copyright © 2013 by ASME
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Fig. 1

Schematic of Karlsruhe preswirl rig (Bricaud et al. [24])

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Fig. 2

Steady and unsteady models for the Karlsruhe rig

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Fig. 3

Unsteady monitor probe locations

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Fig. 4

Converge history for moment on the stator wall inside the chamber

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Fig. 5

Time averaged CD values

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Fig. 6

Swirl velocity inside the preswirl chamber

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Fig. 7

Total temperature drop for the Karlsruhe rig at ∼7000 rpm

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Fig. 8

Fluid and solid domains for the coupled model

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Fig. 9

CFD model and, estimated, and calculated heat flux for the labyrinth seal

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Fig. 10

Rotor disk temperatures

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Fig. 11

Radial variation of circumferential averaged Nusselt number

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Fig. 12

Comparison of Nusselt numbers from the coupled calculations




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