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A fully distributed unstructured Navier-Stokes solver for large-scale aeroelasticity computations

Published online by Cambridge University Press:  04 July 2016

G. Barakos ,
M. Vahdati ,
A.I. Sayma ,
C. Bréard  and
M. Imregun
G. Barakos
Affiliation:
Centre for Vibration Engineering Mechanical Engineering Department, Imperial College of Science, Technology and Medicine, London, UK
M. Vahdati
Affiliation:
Centre for Vibration Engineering Mechanical Engineering Department, Imperial College of Science, Technology and Medicine, London, UK
A.I. Sayma
Affiliation:
Centre for Vibration Engineering Mechanical Engineering Department, Imperial College of Science, Technology and Medicine, London, UK
C. Bréard
Affiliation:
Centre for Vibration Engineering Mechanical Engineering Department, Imperial College of Science, Technology and Medicine, London, UK
M. Imregun
Affiliation:
Centre for Vibration Engineering Mechanical Engineering Department, Imperial College of Science, Technology and Medicine, London, UK
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Abstract

This paper presents the development and validation of a parallel unsteady flow and aeroelasticity code for large-scale numerical models used in turbo machinery applications. The work is based on an existing unstructured Navier-Stokes solver developed over the past ten years by the Aeroelasticity Research Group at Imperial College Vibration University Technology Centre. The single-process multiple-data paradigm was adopted for the parallelisation of the solver and several validation cases were considered. The computational mesh was divided into several sub-sections using a domain decomposition technique. The performance and numerical accuracy of the parallel solver was validated across several computer platforms for various problem sizes. In cases where the solution could be obtained on a single CPU, the serial and parallel versions of the code were found to produce identical results. Studies on up to 32 CPUs showed varying levels of parallelisation efficiency, an almost linear speed-up being obtained in some cases. Finally, an industrial configuration, a 17 blade row turbine with a 47 million point mesh, was discussed to illustrate the potential of the proposed large-scale modelling methodology.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1050 , August 2001 , pp. 419 - 426
Copyright
Copyright © Royal Aeronautical Society 2001 

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