Abstract: Turbomachine with an annular combustion chamber including at its upstream end an annular chamber bottom, and attached at its downstream end by annular flanges to a radially inner casing and outer casing, wherein the upstream end of the chamber is connected to the inner casing or outer casing by elastically deformable bridges.

Abstract: Annular combustion chamber for a turbomachine, comprising two cylindrical walls these being a radially internal and a radially external wall and fixed by bolting at their upstream ends (46, 48) to an internal (54) and an external (56) annular flange of an annular chamber end wall, and an annular fairing extending in the upstream direction from the chamber end wall, and in which the internal (50) and external (52) annular ends are fixed by bolting to the flanges of the chamber end wall in axial alignment with the annular ends (46, 48) of the walls of the chamber.

Abstract: Turbomachine with an annular combustion chamber (46) comprising at its upstream end an annular chamber bottom (28), and attached at its downstream end by annular flanges (24, 26) to a radially inner casing (14) and outer casing (18), wherein the upstream end of the chamber (46) is connected to the inner casing (14) or outer casing (18) by elastically deformable means (48, 49) of variable stiffness.

Abstract: An annular fairing for covering the annular chamber end wall of a turbomachine combustion chamber, and in particular of an airplane turbojet. The fairing presents openings for passing fuel injectors that are supported by the chamber end wall. The fairing is subdivided into a plurality of adjacent sectors, each sector presenting inner and outer fastener edges capable of being fastened on either side of said chamber end wall. Each sector includes a lip on one of its side edges, which lip is connected to the remainder of the sector by a step, said lip being designed to over the side edge of the adjacent sector.

Abstract: A turbomachine combustion chamber has primary and dilution air inlet orifices formed by die stamping to have edges that project into the inside of the combustion chamber, and stress relaxation and/or reduction means in the edges or in the vicinity of the edges of said orifices, said means comprising, for each orifice, one, two, or three slots formed in the edge or around a fraction of the edge of said orifice.

Abstract: Annular combustion chamber of a turbomachine, including an inner wall, an outer wall (28) and a chamber bottom (30) arranged between said walls in the upstream region of said chamber, in which the chamber bottom (30) is divided into several adjacent sectors (130), each sector being attached to said walls (28), these sectors (130) presenting lateral edges such that the lateral edges (130a, 130b) of two adjacent sectors overlap. More precisely, each sector (130) includes a lip (60) extending along one of its lateral edges (130a), this lip projecting relative to one of the faces of this sector and covering the lateral edge (130b) of the adjacent sector.

Abstract: Annular combustion chamber (24) of a turbomachine, including an inner wall, an outer wall (28), a chamber bottom (30) disposed between said walls in the upstream region of said chamber, and two attachment flanges (27, 29) disposed downstream of the chamber bottom and respectively enabling said walls to be attached to other parts of the turbomachine, each wall being divided into several adjacent sectors (128) and each sector being attached to the chamber bottom and to one of the attachment flanges. Advantageously, said adjacent sectors (128) overlap at their lateral edges and there exists a degree of radial play between two adjacent sectors. In addition, the lateral edges (128a, 128b) of the sectors (128) are inclined circumferentially relative to the principal axis of the combustion chamber.

Abstract: The invention concerns a turbine engine annular combustion chamber made up of inner (6) and outer (8) longitudinal walls connected upstream by a transverse chamber bottom (10) and comprising a single-piece cowling (12) covering said chamber bottom, the longitudinal walls (6, 8) each being inserted between corresponding flanges (22, 24; 26, 28) of the chamber bottom (10) and of the cowling (12). The longitudinal walls (6, 8), the chamber bottom (10) and the cowling (12) are assembled together by means of a plurality of first fixings (20a; 20b) between the longitudinal walls (6, 8) and the chamber bottom (10) alternating with a plurality of second fixings (20a; 20b) distinct from the first fixings between the longitudinal walls (6, 8) and the cowling (12).