US 12,313,081 B2
Module for mounting a turbomachine fan blade
Caroline Marie Frantz, Moissy-Cramayel (FR); Vincent François Georges Millier, Moissy-Cramayel (FR); and Jean Charles Olivier Roda, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/711,438
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Nov. 16, 2022, PCT No. PCT/FR2022/052109
§ 371(c)(1), (2) Date May 17, 2024,
PCT Pub. No. WO2023/089274, PCT Pub. Date May 25, 2023.
Claims priority of application No. 2112278 (FR), filed on Nov. 19, 2021.
Prior Publication US 2025/0020139 A1, Jan. 16, 2025
Int. Cl. F04D 29/36 (2006.01); B64C 11/06 (2006.01)
CPC F04D 29/362 (2013.01) [B64C 11/06 (2013.01); F05D 2220/36 (2013.01); F05D 2260/74 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A module for mounting a turbomachine fan blade comprising:
a blade force take-up device,
a blade support intended to support a fan blade and able to pivot about a radial axis, the blade support being configured to be engaged axially along the radial axis inside the blade force take-up device, the blade support and the blade force take-up device being mutually configured to ensure both a clamping of the blade support against the device and an axial retention along the radial axis of the blade support inside the device in order to prevent any movement of axial disengagement of the blade support relative to the device, the blade support and the device each including, on their respective surfaces intended to cooperate with each other, an alternation of conical seats and recesses making it possible when the recesses of one of the two respective surfaces are in geometric correspondence with the conical seats of the other surface, to axially slide the blade support relative to the device and when the conical seats of the two respective surfaces are in geometric correspondence with each other, to prevent any axial sliding movement of the blade support relative to the device.