US 12,334,719 B2
Turbine engine comprising improved harness support means
Patrice Gaspar, Moissy-Cramayel (FR); Samy Alexandre Hoballah, Moissy-Cramayel (FR); Cyrille François Antoine Mathias, Moissy-Cramayel (FR); Khy Tan, Moissy-Cramayel (FR); and Edouard Thebaud, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/246,519
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Sep. 28, 2021, PCT No. PCT/FR2021/051666
§ 371(c)(1), (2) Date Mar. 24, 2023,
PCT Pub. No. WO2022/064160, PCT Pub. Date Mar. 31, 2022.
Claims priority of application No. 2009815 (FR), filed on Sep. 28, 2020.
Prior Publication US 2023/0369838 A1, Nov. 16, 2023
Int. Cl. F01D 25/24 (2006.01); F16L 3/223 (2006.01); H02G 3/00 (2006.01)
CPC H02G 3/26 (2013.01) [F01D 25/24 (2013.01); F16L 3/2235 (2013.01); F05D 2260/31 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An aircraft turbine engine with a main axis comprising:
an arm that is radial with respect to the main axis extending throughout an air flow duct;
a support wall belonging to the radial arm and which includes two openings;
a plurality of harnesses partially extending throughout the radial arm and a section of each harness of which is fastened to said support wall of the arm; and
two mounting blocks, each mounting block of the two mounting blocks is associated with a group of sections of the harnesses.