ANNULAR COMBUSTION CHAMBER OF TURBO-MACHINE Russian patent published in 2018 - IPC F23R3/60 F23R3/52 

FIELD: machine building.

SUBSTANCE: invention relates to the region of the turbomachine combustion chambers, and in particular to the region of annular combustion chambers for the turbomachine and, in particular, but not exclusively, for the helicopter turboshaft engine. Annular combustion chamber for the turbomachine, which has the axial direction (X), the radial direction (R) and the azimuth direction (Y) and comprises the first annular wall (12) and the second annular wall (14), wherein each wall constraints at least part of the volume of the annular combustion chamber. First and the second walls (12, 14) have reciprocal connecting elements (12d, 14d), wherein the first wall (12) comprises at least one first through opening (12f), and the second wall (14) comprises at least one second through opening (14f). Where the combustion chamber also comprises at least one pin, which is engaged with the pair of openings that includes the first opening (12f) and the second opening (14f). Also, the mentioned pin (18) locks the connection of the first and the second walls (12, 14). Turbomachine that comprises the combustion chamber is also provided.

EFFECT: invention allows to facilitate assembling of the combustion chamber, and also allows to facilitate locking of the connection of its walls without any need for welding or the use of bolts.

9 cl, 4 dwg