US 12,459,657 B2
Structure for linking and supporting a turbine engine on an aircraft pylon
Guillaume Glemarec, Moissy-Cramayel (FR); Bruno Albert Beutin, Moissy-Cramayel (FR); Valerio Capasso, Moissy-Cramayel (FR); and Jean-Baptiste Manuel Nicolas Vignes, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/562,235
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed May 17, 2022, PCT No. PCT/FR2022/050931
§ 371(c)(1), (2) Date Nov. 17, 2023,
PCT Pub. No. WO2022/248791, PCT Pub. Date Dec. 1, 2022.
Claims priority of application No. 2105534 (FR), filed on May 27, 2021.
Prior Publication US 2024/0239502 A1, Jul. 18, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. B64D 27/40 (2024.01); F01D 25/28 (2006.01)
CPC B64D 27/40 (2024.01) [B64D 27/402 (2024.01); B64D 27/404 (2024.01); B64D 27/406 (2024.01); F01D 25/28 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A structure for linking and supporting a turbine engine to an aircraft pylon, the structure having a first axis of elongation intended to extend parallel to a second axis of elongation of the pylon, the structure comprising:
a first axial segment for fastening to the pylon, this first segment comprising an upper end which defines a substantially horizontal plane of interface with the pylon, and a lower end carrying suspension connecting rods which are intended to be connected to the turbine engine and which extend in a first substantially vertical plane, referred to as the rear plane, and
a second axial segment which is intended to extend in front of the pylon and comprising at least one suspension member which is intended to be connected to the turbine engine and which extends in a second substantially vertical plane, referred to as the front plane, this front plane being at an axial distance from the rear plane,
wherein the second segment comprises an upper platform for fastening at least one root of a rectifier vane.