Aeronautic propulsion system with improved propulsion efficiency
AssigneesSafran Aircraft Engines, Safran Transmission Systems
InventorsMaeva Daphné Gros-Borot, Gilles Alain Marie Charier, Matthieu Bruno François Foglia, Caroline Marie Frantz, Adrien Louis Simon
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Abstract
An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.
Claims16
A propulsion system comprising:
- a drive shaft movable in rotation about an axis of rotation;
- a low-pressure compressor driven in rotation by the drive shaft, said low-pressure compressor having a predetermined mean radius;
- a fan shaft;
- a fan driven in rotation by the fan shaft;
- a reduction mechanism coupling the drive shaft and the fan shaft, the reduction mechanism comprising a first reduction stage driven by the drive shaft and a second reduction stage that drives the fan shaft and having a reduction ratio;
- and an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet channel having a mean radius;
- wherein a first ratio between a ratio of the mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.
Dependencies are inferred from the claim text.