Virtual Integrated Fan and Turbine

Purpose and goal:

Important learnings have been made regarding the approach and methods used for noise level estimation from a turbofan engine. Noise levels have been estimated for an engine using a high-fidelity method based on detailed CFD simulations, as well as a low-fidelity system level model. Experimental results for a carbon fibre fan blade has been utilized for validation of a structural analysis tool.

Working on a common virtual engine platform has been very beneficial for knowledge sharing between industry and the universities in the project. Expected results and effects:

The aerodynamic design was updated for the fan blades, outlet guide vanes, nacelle, low-pressure turbine and the turbine rear structure of a virtual turbofan engine. Different carbon fibre layups were numerically evaluated for a fan blade. The new designs were incorporated into the whole engine CAD model developed by the project partners as part of this, and earlier, projects.

Methods for assessment of aircraft engine noise levels were explored in the project, and an assessment of the noise level of the virtual engine was performed. Approach and implementation:

The project was coordinated by GKN Aerospace. Two in-person meetings were organized, where representatives from all project partners attended. On-line meetings were held when needed to discuss work in the various work packages throughout the project. The development of a common virtual engine platform contribute to a lot of partner interaction, as design changes, choices and new results often impact other components and project partners.