Fan blade with zero tip dihedral at the head

Patent metadata

Field	Value
Publication number	US-2023392502-A1
Application number	US-202118032763-A
Country	US
Kind code	A1
Filing date	Oct 19, 2021
Priority date	Oct 20, 2020
Publication date	Dec 7, 2023
Grant date	—

Abstract

The present invention relates to a blade ( 3 ) of a fan ( 1 ), made of composite material, of a turbomachine. On a portion ( 15 ) of the blade ( 7 ) which extends from a lower limit ( 16 ) located at a predetermined distance (d) from the shank ( 6 ) of the blade equal to at least 80% of the predetermined height (h) to the top ( 11 ) of the blade ( 7 ), a dihedral angle (D) measured at at least one predefined point on the chord of the blade ( 3 ), located on the chord of the blade ( 3 ) at the upstream end ( 13 a ) of the nose ( 13 ) of the shield ( 12 ), is greater than or equal to −3° and less than or equal to 0°.

First claim

1 . A Turbomachine fan blade comprising:
a structure of composite material comprising a fibrous reinforcement obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement is embedded, the composite material structure comprising an airfoil with an aerodynamic profile able to extend in an air flow, comprising a leading edge and a trailing edge, a root configured to be attached to a fan disk and a support extending between the root and the airfoil, the airfoil having a predetermined height between the support and a top of the airfoil along a stacking axis; and a metallic shield applied and attached to the leading edge of the airfoil, the metallic shield comprising a nose attached to the leading edge;
a chord of the blade being defined, in a plane normal to the stacking axis, between an upstream end of the nose of the shield and the trailing edge;
wherein

on a portion of the airfoil which extends from a lower limit located at a predetermined distance from the support at least equal to 80% of the predetermined height the top of the airfoil, a dihedral angle measured at one predefined point at least of the chord of the blade, located on the chord of the blade at the upstream end of the nose of the shield, is greater than or equal to −3° and less than or equal to 0°.

2 . The turbomachine fan blade according to claim 1 , wherein the nose and the fins of the shield delimit together a cavity housing the leading edge of the airfoil and the predefined point of the chord is located within the cavity.

3 . The turbomachine fan blade according to claim 1 , wherein the dihedral angle is greater than or equal to −3° and less than or equal to 0° at several predefined points of the chord of the blade within the portion of the blade

4 . The turbomachine fan blade according to claim 1 wherein, within the portion, the dihedral angle is greater than or equal to −3° and less than or equal to 0° over a distance at least equal to 10% of the predetermined height, preferably over a distance at least equal to 15% of the predetermined height.

5 . The turbomachine fan blade according to claim 1 wherein, within the portion, the dihedral angle is greater than or equal to −3° and less than or equal to 0° over the entire height of the portion 15 .

6 . The turbomachine fan blade according to claim 1 , wherein, within the portion, a variation of the dihedral angle along the stacking axis over a distance equal to 10% of the height of the airfoil is equal to 3° at most.

7 . The turbomachine fan blade according to claim 1 , wherein, within the portion, the dihedral angle is greater than or equal to −2° and less than or equal to 0°, preferably greater than or equal to −1° C. and less than or equal to 0°.

8 . The turbomachine fan blade according to claim 1 , wherein the fins extend over a length greater than or equal to 15% and less than or equal to 25% of a chord length of the airfoil.

9 . A fan for a turbomachine comprising a plurality of turbomachine fan blades according to claim 1 .

10 . The fan according to claim 9 , comprising at most twenty fan blades.

11 . The fan according to claim 9 , having an outer diameter of the fan comprised between eighty inches and one hundred inches, preferably between eighty inches and ninety inches.

12 . A turbomachine comprising a fan according to claim 9 .

13 . The turbomachine according to claim 12 having a bypass ratio greater than or equal to 10, for example comprised between 10 and 80 inclusive.

14 . An aircraft comprising at least one turbomachine according to claim 12 .

Assignees

• Safran Aircraft Engines

Inventors

• Gondre Guillaume Pascal Jean-Charles
• MAHIAS Stéphane Roger
• Bazot Olivier
• Belmon Guillaume Claude Robert
• Sullet Charles-Henri Claude Jacky

Classifications

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05D2300/6034

  Orientation of fibres, weaving, ply angle · CPC title

• F05D2250/38

  angled, e.g. sweep angle · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title