Blade for a ducted fan of a turbomachine
AssigneeSafran Aircraft Engines
InventorMatthieu Pierre Michel DUBOSC
Life of this patent
Estimating the term…
Abstract
A blade for a ducted fan of a turbomachine includes an airfoil formed of plural airfoil sections stacked along an airfoil axis. A difference in sweep corresponding to a difference between a leading edge sweep and a trailing edge sweep of an airfoil section is substantially identical for any airfoil section having a height of between 10% and 20% of an airfoil height of the airfoil, and/or substantially identical for any airfoil section having a height of between 75% and 90% of the airfoil height.
Claims20
1-9. (canceled)
A blade for a ducted fan of a turbomachine, the turbomachine extending around a longitudinal axis, the blade comprising an airfoil with an aerodynamic profile having a leading edge and a trailing edge, the airfoil being formed of a plurality of airfoil sections stacked along an airfoil axis from a radially inner end to a radially outer end of the airfoil, an airfoil height corresponding to a distance along the airfoil axis from the radially inner end to the radially outer end of the airfoil,
- wherein each airfoil section comprises a leading edge sweep corresponding to an angle between the airfoil axis and a median segment of the leading edge within said airfoil section,
- wherein each airfoil section comprises a trailing edge sweep corresponding to an angle between the airfoil axis and a median segment of the trailing edge within said airfoil section,
- wherein a sweep difference of an airfoil section is defined as a difference between the leading edge sweep and the trailing edge sweep,
- wherein the sweep difference of an airfoil section is:
- negative, the sweep difference being strictly less than 0° and being moreover greater than −30°, when the airfoil section has a height comprised between 10% and 40% of the airfoil height,
- positive, the sweep difference being strictly greater than 0° and being moreover less than +40°, when the airfoil section has a height comprised between 60% and 90% of the airfoil height, and
- substantially identical for any of the airfoil sections having a height comprised between 10% and 20% of the airfoil height.
A blade for a ducted fan of a turbomachine, the turbomachine extending around a longitudinal axis, the blade comprising an airfoil with an aerodynamic profile having a leading edge and a trailing edge, the airfoil being formed of a plurality of airfoil sections stacked along an airfoil axis from a radially inner end to a radially outer end of the airfoil, an airfoil height corresponding to a distance along the airfoil axis from the radially inner end to the radially outer end of the airfoil,
- wherein each airfoil section comprises a leading edge sweep corresponding to an angle between the airfoil axis and a median segment of the leading edge within said airfoil section,
- wherein each airfoil section comprises a trailing edge sweep corresponding to an angle between the airfoil axis and a median segment of the trailing edge within said airfoil section,
- wherein a sweep difference of an airfoil section is defined as a difference between the leading edge sweep and the trailing edge sweep,
- wherein the sweep difference of an airfoil section is:
- negative, the sweep difference being strictly less than 0° and being moreover greater than −30°, when the airfoil section has a height comprised between 10% and 40% of the airfoil height,
- positive, the sweep difference being strictly greater than 0° and being moreover less than +40°, when the airfoil section has a height comprised between 60% and 90% of the airfoil height, and
- substantially identical for any of the airfoil sections having a height comprised between 75% and 90% of the airfoil height.
Dependencies are inferred from the claim text.