US 12,404,821 B2
Suspension of a triple-flow aircraft turbine engine
Guillaume Glemarec, Moissy-Cramayel (FR); Nicolas Maurice Herve Aussedat, Moissy-Cramayel (FR); Pierre Charles Caruel, Moissy-Cramayel (FR); Mathieu Marc Christian Gaillot, Moissy-Cramayel (FR); and Jean-Baptiste Manuel Nicolas Vignes, Moissy-Cramayel (FR)
Assigned to GENERAL ELECTRIC COMPANY, Schenectady, NY (US); SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
Appl. No. 18/852,382
Filed by GENERAL ELECTRIC COMPANY, New York, NY (US); SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
PCT Filed Apr. 15, 2022, PCT No. PCT/FR2022/050719
§ 371(c)(1), (2) Date Sep. 27, 2024,
PCT Pub. No. WO2023/198962, PCT Pub. Date Oct. 19, 2023.
Prior Publication US 2025/0215830 A1, Jul. 3, 2025
Int. Cl. F02C 7/20 (2006.01); F02K 3/077 (2006.01)
CPC F02C 7/20 (2013.01) [F02K 3/077 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and comprising:
a gas generator comprising at least one compressor, an annular combustion chamber, and at least one turbine,
at least one main propeller rotated by a shaft of the gas generator,
the gas generator comprising:
a first annular splitter nose for separating two annular ducts for the respective flow of an internal primary flow inside the gas generator and an external secondary flow around the gas generator,
a second annular splitter nose for separating two annular ducts for the respective flow of a first internal flow and of a second external flow,
a first nozzle for ejecting the first internal flow,
a second nozzle for ejecting the second external flow,
a first annular compartment, referred to as hot compartment, extending axially between the second splitter nose and the first nozzle, and between first and second annular walls, respectively internal and external, which extend around each other, the first wall externally defining said duct for the flow of the first internal flow, and said second wall internally defining said duct for the flow of the second external flow,
a second annular compartment, referred to as cold compartment, extending axially between the first splitter nose and the second nozzle, and between third and fourth annular walls, respectively internal and external, which extend around each other, the third wall externally defining said duct for the flow of the second external flow, and said fourth wall internally defining said duct for the flow of the secondary flow,
upstream suspension members of the turbine engine, which are located in a first plane perpendicular to said axis and which are connected or attached to the gas generator,
downstream suspension members of the turbine engine, which are located in a second plane perpendicular to said axis and which are connected or attached to the gas generator, and
thrust-absorbing rods which comprise first ends connected or attached to the gas generator and opposite second ends located in a third plane perpendicular to said axis,
wherein said first, second and third planes are located axially between the first splitter nose and the second nozzle, and in that at least one part of said upstream and downstream suspension members are connected or attached to said third wall.