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

Abstract EN

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.