Fan Alternatives for Next Generation engines 2

Purpose and goal

The project Fan Alternatives for Next Generation engines 2 aims to give GKN Aerospace och Chalmers input to design components for energy efficient and environmentally improved aircraft engines. FANG2 develops methods to calculate the geometry and construction of low pressure system in future turbofan engines. The focus is to balance, on the one hand, size, weight and cost of the propulsive fan and the components which support it, and on the other hand, its aerodynamic efficiency and ability to convert shaft power to thrust.

Expected effects and result

Methods to evaluate low pressure systems for future commercial turbofans, in particular stall margin and aerodynamics. A case study for a mid range single aisle aircraft including assessment of the effect of varying engine diameter. Comparison between 3D aeroanalysis and correlation methods for fan function. Optimal specific thrust and fan pressure ratio as well as impact of weight, nacelle drag and component efficiency on the fan design parameters. The project will support pre-studies of components for next generation engines with requirements and environmental conditions.

Planned approach and implementation

FANG2 consists of three work packages: Advanced Fan Aerodynamics, which will generate and simulate three-dimensional geometries for a propulsion fan. The results will be used to calibrate the correlation model, previously developed based on two-dimensional aerodynamic calculations. The aircraft application work package will integrate the fan model into a performance and weight model for an engine to be linked with an aircraft and nacelle model. The coupled model will be evaluated in a mission simulation. In the final work package a PhD thesis will be assembled and defended.