Granted Patent B2

US 12,448,890 · App. 18/713,860 · Granted Oct 21, 2025

Inventor: Matthieu Pierre Michel Dubosc (Moissy-Cramayel, FR)

Assignee: SAFRAN AIRCRAFT ENGINES

F01D5/141F04D29/324F01D5/145F05D2220/32F05D2220/36F05D2240/303F05D2240/304

Abstract

Claims (50)

1. 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:

less than 0° and greater than −30°, when the airfoil section has a height comprised between 10% and 40% of the airfoil height, and

greater than 0° and less than +40°, when the airfoil section has a height comprised between 60% and 90% of the airfoil height, and

wherein the sweep differences

for any of the airfoil sections having a height comprised between 10% and 20% of the airfoil height are identical within +/−1°.

2. The blade as claimed in claim 1 , wherein the sweep difference of an airfoil section is identical for any of the airfoil sections having a height comprised between 75% and 90% of the airfoil height.

3. The blade as claimed in claim 1 , wherein each airfoil section extends over at least 1% and at the most 10% of the airfoil height.

4. The blade as claimed in claim 1 , wherein each airfoil section extends over 5% of the airfoil height.

5. The blade as claimed in claim 1 , wherein the sweep difference changes sign between two airfoil sections each having a height comprised between 40% and 60% of the airfoil height.

6. The blade as claimed in claim 1 , wherein the sweep difference changes sign between two airfoil sections each having a height comprised between 45% and 55% of the airfoil height.

7. The blade as claimed in claim 1 , wherein the sweep difference of an airfoil section is comprised between −25° and −10° when the airfoil section has a height comprised between 10% and 30% of the airfoil height.

8. The blade as claimed in claim 1 , wherein the sweep difference of an airfoil section is comprised between +5° and +25° when the airfoil section has a height comprised between 60% and 90% of the airfoil height.

9. The blade as claimed in claim 1 , wherein the sweep difference increases in a linear manner with the height for airfoil sections having heights ranging from 30% to 60% of the airfoil height.

10. The blade as claimed in claim 1 , wherein the sweep difference increases in a linear manner with the height for airfoil sections having heights ranging between 20% to 70% of the airfoil height.

11. 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:

less than 0° and greater than −30°, when the airfoil section has a height comprised between 10% and 40% of the airfoil height, and

greater than 0° and less than +40°, when the airfoil section has a height comprised between 60% and 90% of the airfoil height, and

wherein the sweep differences

for any of the airfoil sections having a height comprised between 75% and 90% of the airfoil height are identical within +/−1°.

12. A ducted fan for a turbomachine comprising a plurality of the blades as claimed in claim 1 .

13. The ducted fan as claimed in claim 12 , comprising fewer than 23 blades.

14. The ducted fan as claimed in claim 12 , comprising 16 blades.

15. The ducted fan as claimed in claim 12 , comprising 18 blades.

16. The ducted fan as claimed in claim 12 , having a fan pressure ratio between 1.1 and 1.55.

17. A turbomachine comprising the ducted fan as claimed claim 12 , the turbomachine being a bypass turbomachine.

18. A turbomachine comprising the ducted fan as claimed in claim 12 , the turbomachine being a triple flow turbomachine.

19. 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:

less than 0° and greater than −30°, when the airfoil section has a height comprised between 10% and 40% of the airfoil height,

greater than 0° and less than +40°, when the airfoil section has a height comprised between 60% and 90% of the airfoil height, and

greater than +10° and less than +20°, when the airfoil section has a height comprised between 60% and 90% of the airfoil height.

20. 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:

less than 0° and greater than −30°, when the airfoil section has a height comprised between 10% and 40% of the airfoil height, and

greater than 0° and less than +40°, when the airfoil section has a height comprised between 60% and 90% of the airfoil height,

and wherein the sweep difference is increasing in a linear manner within +/−2° with the height for airfoil sections having heights ranging between 20% to 70% of the airfoil height.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (49)