US 12,140,045 B2
Method for balancing fan vanes with trailing edge machining
Pierre-Alexis Poulet, Moissy-Cramayel (FR); Richard Mounien, Moissy-Cramayel (FR); and Lucas Antoine Christophe Lauwick, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/571,688
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 16, 2022, PCT No. PCT/FR2022/051175
§ 371(c)(1), (2) Date Dec. 18, 2023,
PCT Pub. No. WO2022/269173, PCT Pub. Date Dec. 29, 2022.
Claims priority of application No. 2106571 (FR), filed on Jun. 21, 2021.
Prior Publication US 2024/0287909 A1, Aug. 29, 2024
Int. Cl. F01D 5/28 (2006.01)
CPC F01D 5/282 (2013.01) [F05D 2230/10 (2013.01); F05D 2240/303 (2013.01); F05D 2240/304 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A method for manufacturing a vane for a fan of an aircraft turbomachine extending about a longitudinal axis, the vane comprising a blade made of a composite material having a leading edge and a trailing edge connected by a pressure side and a suction side, the blade extending between a root and a free end, the method comprising each of the following steps:
pairing and bonding a metal shield to the leading edge,
obtaining a first measurement of a radial moment weight of the vane before or after bonding the metal shield and determining a machining kerf,
machining the free end and/or the trailing edge along the machining kerf so as to adjust the mass and the radial moment weight of the vane,
obtaining a second measurement of the radial moment weight of the vane.