US 11,971,174 B2
Fastening for a turbomachine combustion chamber
Dan-Ranjiv Joory, Moissy-Cramayel (FR); Jacques Marcel Arthur Bunel, Moissy-Cramayel (FR); and Benjamin Frantz Karl Villenave, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/610,893
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed May 14, 2020, PCT No. PCT/FR2020/050805
§ 371(c)(1), (2) Date Nov. 12, 2021,
PCT Pub. No. WO2020/229781, PCT Pub. Date Nov. 19, 2020.
Claims priority of application No. 1904986 (FR), filed on May 14, 2019.
Prior Publication US 2022/0196243 A1, Jun. 23, 2022
Int. Cl. F23R 3/50 (2006.01)
CPC F23R 3/50 (2013.01) [F23R 2900/00017 (2013.01)] 9 Claims
OG exemplary drawing
 
1. An aircraft gas turbomachine having an axis and comprising an outer housing and an annular combustion chamber having a chamber bottom, the annular combustion chamber comprising an inner annular shroud and an outer annular shroud that are radial with respect to the axis of the turbomachine, arranged one inside the other, and connected at upstream ends by an annular wall of the chamber bottom, the annular combustion chamber being fixed, at an upstream part thereof, to the outer housing, via pins individually connected by a swivel connection,
wherein, at said upstream part of the annular combustion chamber, and for each pin:
the swivel connection is established between the pin and a part of the outer housing in which a convex wall of the pin is received, and
a sliding connection is established, spaced from the swivel connection, between the pin and a part of the outer annular shroud and/or the annular wall of the chamber bottom, the sliding connection providing sliding translation of the pin relative to the outer annular shroud and/or the annular wall of the chamber bottom.