US 12,000,300 B2
Exhaust cone for a turbomachine
Jean-Philippe Joret, Moissy-Cramayel (FR); Vincent Devanlay, Moissy-Cramayel (FR); Marine Ollivier, Moissy-Cramayel (FR); and Guillaume Levieux, Moissy-Cramayel (FR)
Assigned to SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
Appl. No. 18/034,659
Filed by SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
PCT Filed Nov. 3, 2021, PCT No. PCT/FR2021/051936
§ 371(c)(1), (2) Date Apr. 28, 2023,
PCT Pub. No. WO2022/096822, PCT Pub. Date May 12, 2022.
Claims priority of application No. 2011383 (FR), filed on Nov. 5, 2020.
Prior Publication US 2023/0392518 A1, Dec. 7, 2023
Int. Cl. F01D 25/24 (2006.01)
CPC F01D 25/24 (2013.01) [F05D 2260/30 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An assembly for a turbomachine (1) comprising:
an exhaust cone (18) and an exhaust case (17) including an annular inner shell (19), the exhaust cone (18) and the exhaust case (17) extending about an axis (X),
the exhaust cone (18) including a radially outer skin (31) extending in the projection of said inner shell (19) and a radially inner skin (30) defining a chamber (32) with the outer skin (31), an upstream end (33) of the cone (18) being fastened to the inner shell (19) via connecting lugs (39),
the assembly including an annular fairing (29) located radially outside said lugs (39) and extending axially between the inner shell (19) of the exhaust case (17) and the outer skin (31) of the exhaust cone (18), said fairing (29) extending in the projection of said inner shell (19) and of the outer skin (31),
wherein the fairing (29) is segmented and comprises several angular segments (42) arranged circumferentially end to end.