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International Journal of Rotating Machinery
Volume 2011 (2011), Article ID 182906, 8 pages
Research Article

Development of a Method for Enhanced Fan Representation in Gas Turbine Modeling

1Department of Power and Propulsion, SOE, Cranfield University, Bedfordshire MK43 0AL, UK
2Department of Mechanical Engineering, Aristotle University of Thessaloniki, 54124 Thessaloniki, Greece

Received 1 November 2010; Revised 11 May 2011; Accepted 17 May 2011

Academic Editor: M. Razi Nalim

Copyright © 2011 Georgios Doulgeris et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


A challenge in civil aviation future propulsion systems is expected to be the integration with the airframe, coming as a result of increasing bypass ratio or above wing installations for noise mitigation. The resulting highly distorted inlet flows to the engine make a clear demand for advanced gas turbine performance prediction models. Since the dawn of jet engine, several models have been proposed, and the present work comes to add a model that combines two well-established compressor performance methods in order to create a quasi-three-dimensional representation of the fan of a modern turbofan. A streamline curvature model is coupled to a parallel compressor method, covering radial and circumferential directions, respectively. Model testing has shown a close agreement to experimental data, making it a good candidate for assessing the loss of surge margin on a high bypass ratio turbofan, semiembedded on the upper surface of a broad wing airframe.