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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Automatic Optimization of Preswirl Nozzle Design

[+] Author and Article Information
Fabio Ciampoli, John W. Chew

Fluids Research Centre, School of Engineering, University of Surrey, Guildford, Surrey GU2 7XH, UK

Shahrokh Shahpar, Elisabeth Willocq

 Rolls-Royce plc, PO Box 31, Derby DE24 8BJ, UK

J. Eng. Gas Turbines Power 129(2), 387-393 (Feb 01, 2006) (7 pages) doi:10.1115/1.2364194 History: Received October 01, 2005; Accepted February 01, 2006

The objective of the research described here is to develop and demonstrate use of automatic design methods for preswirl nozzles. Performance of preswirled cooling air delivery systems depends critically on the design of these nozzles which is subject to manufacturing and stress constraints. The best solution may be a compromise between cost and performance. Here it is shown that automatic optimization using computational fluid dynamics (CFD) to evaluate nozzle performance can be useful in design. A parametric geometric model of a nozzle with appropriate constraints is first defined and the CFD meshing and solution are then automated. The mesh generation is found to be the most delicate task in the whole process. Direct hill climbing (DHC) and response surface model (RSM) optimization methods have been evaluated. For the test case considered, significant nozzle performance improvements were obtained using both methods, but the RSM model was preferred.

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Copyright © 2007 by American Society of Mechanical Engineers
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Figures

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Figure 1

Parametric representation of nozzle

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Figure 2

Geometric constraints

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Figure 3

CFD domain and meshing strategy

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Figure 4

View of mesh for base line geometry

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Figure 5

Mesh dependency for the base line condition

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Figure 6

Influence of convergence criterion

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Figure 7

Influence of the number of multigrid levels on computing time

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Figure 8

Influence of the number of processors used on the compute time

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Figure 11

Execution history of the DHC method

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Figure 12

Execution history of the RMS method

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Figure 13

Nozzle geometries

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