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

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dc.contributor.authorDoulgeris, Georgios C.
dc.contributor.authorKhaleghi, H.
dc.contributor.authorKalfas, A.
dc.contributor.authorPilidis, Pericles
dc.date.accessioned2012-06-21T09:48:51Z
dc.date.available2012-06-21T09:48:51Z
dc.date.issued2011
dc.description.abstractA 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, semi-embedded on the upper surface of a broad wing airframe.en_UK
dc.identifier.citationG Doulgeris, H Khalleghi, A Kalfas and P Pilidis, Development of a Method for Enhanced Fan Representation in Gas Turbine Modeling, International Journal of Rotating Machinery, IJRM/182906, 2011.en_UK
dc.identifier.urihttp://dspace.lib.cranfield.ac.uk/handle/1826/7259
dc.language.isoenen_UK
dc.subjectInlet distortionen_UK
dc.subjectParallel compressoren_UK
dc.titleDevelopment of a Method for Enhanced Fan Representation in Gas Turbine Modelingen_UK
dc.typeArticleen_UK

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