摘要
The aim of this paper is to present the state-of-the art in computational aeroelasticity methods that are available for analyzing fan blades on modern civil aircraft. Fan blades in modern high-bypass aero-engines typically produce around 80% of the thrust. In order to improve specific fuel consumption and reduce the level of noise emitted from the engine, civil turbofan engine designs are moving toward even larger fan diameters with lower tip speeds and hence the importance of this component of aero-engine becomes even more prominent. To reduce weight, future fan blades will be made of composite materials and shorter intakes are used. The new designs are highly loaded and will be more susceptible to aerodynamic and aeroelastic instabilities, and hence computationally efficient aeroelastic modelling tools for such blades are paramount.
The aim of this paper is to present the state-of-the art in computational aeroelasticity methods that are available for analyzing fan blades on modern civil aircraft. Fan blades in modern high-bypass aero-engines typically produce around 80% of the thrust. In order to improve specific fuel consumption and reduce the level of noise emitted from the engine, civil turbofan engine designs are moving toward even larger fan diameters with lower tip speeds and hence the importance of this component of aero-engine becomes even more prominent. To reduce weight, future fan blades will be made of composite materials and shorter intakes are used. The new designs are highly loaded and will be more susceptible to aerodynamic and aeroelastic instabilities, and hence computationally efficient aeroelastic modelling tools for such blades are paramount.
出处
《风机技术》
2018年第5期42-52,共11页
Chinese Journal of Turbomachinery
