US 12,313,003 B2
Fuel distribution assembly for a turbomachine
Sébastien Christophe Loval, Moissy-Cramayel (FR); Pierre Jean-Baptiste Metge, Moissy-Cramayel (FR); Alexandre Corsaut, Moissy-Cramayel (FR); Kevin Auber, Moissy-Cramayel (FR); Marc Serrau, Moissy-Cramayel (FR); and Sébastien Jahin, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/716,550
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Dec. 4, 2022, PCT No. PCT/FR2022/052240
§ 371(c)(1), (2) Date Jun. 5, 2024,
PCT Pub. No. WO2023/105146, PCT Pub. Date Jun. 15, 2023.
Claims priority of application No. 2113214 (FR), filed on Dec. 9, 2021.
Prior Publication US 2025/0043728 A1, Feb. 6, 2025
Int. Cl. F02C 7/22 (2006.01)
CPC F02C 7/222 (2013.01) 19 Claims
OG exemplary drawing
 
1. A fuel distribution assembly (11) for a turbomachine, the distribution assembly (11) extending between a first interface plane (P1) and a second interface plane (P2) substantially parallel to the first interface plane (P1), the distribution assembly (11) comprising a plurality of distribution ducts (13), each duct (13) comprising:
at least one inlet portion (15) that is open to the first interface plane (P1) or to the second interface plane (P2),
at least one outlet portion (19) that is open to the first interface plane (P1) or to the second interface plane (P2), and
a middle portion (17) fluidly connecting each inlet portion (15) of the duct (13) and each outlet portion (19) of the duct (13),
characterized in that the middle portion (17) of each duct (13) has an internal cross-section(S) of substantially elliptical shape,
wherein the distribution assembly (11) comprises a support plate (23) interconnecting the middle portions (17) of the ducts (13), the support plate (23) extending along a midplane (P) substantially parallel to the first interface plane (P1) and to the second interface plane (P2).