US 12,435,633 B2
Fan blade with zero tip dihedral at the head
Guillaume Pascal Jean-Charles Gondre, Moissy-Cramayel (FR); Stéphane Roger Mahias, Moissy-Cramayel (FR); Olivier Bazot, Moissy-Cramayel (FR); Guillaume Claude Robert Belmon, Moissy-Cramayel (FR); and Charles-Henri Claude Jacky Sullet, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/032,763
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Oct. 19, 2021, PCT No. PCT/FR2021/051814
§ 371(c)(1), (2) Date Apr. 19, 2023,
PCT Pub. No. WO2022/084615, PCT Pub. Date Apr. 28, 2022.
Claims priority of application No. FR2010762 (FR), filed on Oct. 20, 2020.
Prior Publication US 2023/0392502 A1, Dec. 7, 2023
Int. Cl. F01D 5/14 (2006.01)
CPC F01D 5/141 (2013.01) [F05D 2250/38 (2013.01); F05D 2300/6034 (2013.01)] 15 Claims
OG exemplary drawing
 
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 forming an airfoil with an aerodynamic profile comprising a leading edge, a trailing edge, a root configured to be attached to a fan disk of the turbomachine fan and a shank extending between the root and the airfoil, the airfoil having a predetermined height between the shank 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 and fins that delimit with the nose a cavity housing the leading edge of the airfoil;
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 the airfoil further comprises a portion, which extends from a lower limit to the top of the airfoil, wherein the lower limit is located at a predetermined distance from the shank at least equal to 80% of the predetermined height,
wherein a dihedral angle is greater than or equal to −3° and less than or equal to 0° in the portion of the airfoil over a distance at least equal to 10% of the predetermined height,
wherein the dihedral angle is a local direction difference between a gas flow through the turbomachine and the blade in projection in a plane that is axial and tangent to the direction of rotation of the turbomachine,
wherein the dihedral angle is measured along the leading edge, wherein the dihedral angle changes sign at least one time along the leading edge from the shank to the top of the airfoil.