US 12,296,967 B2
Assembly comprising an aircraft turbine engine and mounting pylon thereof
Guillaume Glemarec, Moissy-Cramayel (FR); Jean-Baptiste Vignes, Moissy-Cramayel (FR); Romuald Muriel Gentils, Moissy-Cramayel (FR); and Valerio Capasso, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/260,923
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jan. 13, 2022, PCT No. PCT/FR2022/050074
§ 371(c)(1), (2) Date Jul. 10, 2023,
PCT Pub. No. WO2022/157443, PCT Pub. Date Jul. 28, 2022.
Claims priority of application No. 2100556 (FR), filed on Jan. 21, 2021.
Prior Publication US 2024/0052781 A1, Feb. 15, 2024
Int. Cl. B64D 27/40 (2024.01); B64D 27/10 (2006.01); F02C 7/20 (2006.01)
CPC B64D 27/404 (2024.01) [B64D 27/10 (2013.01); B64D 27/40 (2024.01); B64D 27/402 (2024.01); F02C 7/20 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An assembly comprising an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft,
the turbine engine having a longitudinal axis and comprising a gas generator comprising, from upstream to downstream, in the flowing orientation of the gases, at least one compressor, an annular combustion chamber and at least one turbine,
the pylon having a generally elongate shape along said axis and comprising members for suspending the turbine engine, said members being connected to the turbine engine in at least one first plane which is perpendicular to the axis and which is located upstream of the combustion chamber so that the turbine engine is attached in a cantilever manner to the pylon,
wherein the assembly further comprises at least one damper which connects the turbine engine to the pylon and which is located in a second plane perpendicular to the axis located downstream of the combustion chamber, said at least one damper being configured to limit the relative displacements in said second plane between the turbine engine and the pylon,
wherein the at least one damper comprises at least two links, a first link comprising a first end hinged to the pylon and a second link comprising a first end hinged to the turbine engine, the first and second links comprising second ends which are connected together by a damping device, the first and second ends of the links having hinge axes parallel to each other and to the longitudinal axis of the turbine engine.