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International Journal of Turbo & Jet-Engines

Ed. by Sherbaum, Valery / Erenburg, Vladimir


IMPACT FACTOR 2018: 0.863

CiteScore 2018: 0.66

SCImago Journal Rank (SJR) 2018: 0.211
Source Normalized Impact per Paper (SNIP) 2018: 0.625

Online
ISSN
2191-0332
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Volume 36, Issue 3

Issues

A Preliminary Design System for Turbine Discs

Yannick Ouellet / Christian Savaria / François Roy / Hany Moustapha / François Garnier
Published Online: 2017-01-31 | DOI: https://doi.org/10.1515/tjj-2016-0067

Abstract

In order to improve product development cycle, design engineers use multidisciplinary analysis tools which allow for better productivity. This paper covers the development of new tools to improve the preliminary design phase of turbine disc, being a critical part of aircraft engines. First, a new single platform D&A (Design & Analysis) tool integrating commercial CAD (Computer Aided Design) and FEA (Finite Element Analysis) software processing in batch mode is presented. This integrated architecture leads to a real improvement, enabling a cohesive single integrated simulation environment that offers significant time reduction on user manipulation and execution. An optimization of disc geometry is then performed by using different optimization algorithms and configurations for a given disc parameterized model. The results show potential improvement over the current preliminary rotor discs for life and burst limited design. Finally, optimal curves obtained by developing HPT (High Pressure Turbine) disc reference charts, indicate how to get the minimum weight for given mechanical performance without running any structural analysis. These new tools supporting disc design have allowed improvement of disc life and durability leading to a reduction of preliminary design phase duration.

Keywords: high-pressure turbine; disc; preliminary design; gas turbine; system integration

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About the article

Received: 2016-11-02

Accepted: 2016-12-06

Published Online: 2017-01-31

Published in Print: 2019-08-27


This work was funded by Pratt and Whitney Canada (P&WC) and the National Sciences and Engineering Research Council of Canada (NSERC). The authors would like to thank them for their contribution to this project.


Citation Information: International Journal of Turbo & Jet-Engines, Volume 36, Issue 3, Pages 329–338, ISSN (Online) 2191-0332, ISSN (Print) 0334-0082, DOI: https://doi.org/10.1515/tjj-2016-0067.

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