US 12,084,190 B2
Aircraft turbine engine
Regis Eugene Henri Servant, Moissy-Cramayel (FR); Didier Gabriel Bertrand Desombre, Moissy-Cramayel (FR); and Christophe Paul Jacquemard, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/754,078
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Sep. 25, 2020, PCT No. PCT/FR2020/000243
§ 371(c)(1), (2) Date Mar. 23, 2022,
PCT Pub. No. WO2021/058882, PCT Pub. Date Apr. 1, 2021.
Claims priority of application No. 1910693 (FR), filed on Sep. 27, 2019.
Prior Publication US 2022/0340290 A1, Oct. 27, 2022
Int. Cl. F02C 7/36 (2006.01); B64D 27/10 (2006.01)
CPC B64D 27/10 (2013.01) [F02C 7/36 (2013.01); F05D 2220/323 (2013.01); F05D 2260/98 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An aircraft turbine engine, comprising a gas generator comprising at least one annular gas flow duct, the duct being defined by two annular casings, respectively external and internal, extending one around the other and connected together by at least one tubular arm for the passage of a lubricating oil line, wherein the line comprises a first fixed section secured to the external casing, a second fixed section secured to a piece of equipment of the turbine engine capable of moving or vibrating during operation relative to said casings, and an intermediate section extending between said first and second sections, said intermediate section having a generally elongated shape and comprising a first longitudinal end which is engaged and suitable to swivel and slide in an end of said first section through a first ball joint system and a second longitudinal end which is opposite to said first longitudinal end and which is engaged and suitable to swivel and slide in an end of said second section through a second ball joint system.