ANNULAR WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING COOLING ORIFICES CONDUCIVE TO COUNTER-ROTATION
An annular wall for a turbomachine combustion chamber is disclosed, comprising cooling orifices through which cooling air can circulate through the annular wall, each having an air injection axis oriented orthogonal to a longitudinal axis of the annular wall. The cooling orifices are distributed into first annular rows of cooling orifices oriented in a first circumferential direction from an outer face as far as an inner face of the annular wall, and second annular rows of cooling orifices oriented in a second circumferential direction opposite the first circumferential direction from the outer face as far as the inner face of said annular wall. The first annular rows and the second annular rows of cooling orifices are arranged alternately along the longitudinal axis.
1 . Annular wall for a turbomachine combustion chamber comprising cooling orifices through which cooling air can circulate through the annular wall, each having an air injection axis oriented orthogonal to a longitudinal axis of the annular wall, in which the cooling orifices are distributed into first annular rows of cooling orifices oriented in a first circumferential direction from an outer face as far as an inner face of said annular wall, and second annular rows of cooling orifices oriented in a second circumferential direction opposite the first circumferential direction from the outer face as far as the inner face of said annular wall, wherein the first annular rows and the second annular rows of cooling orifices are arranged alternately along the longitudinal axis.
2 . Annular wall according to claim 1 , in which the cooling orifices in each annular row are offset circumferentially from the cooling orifices in the or each consecutive annular rows of cooling orifices, such that all cooling orifices are staggered.
3 . Annular wall according to claim 1 , comprising the same number of first annular rows and second annular rows of cooling orifices.
4 . Annular combustion chamber for a turbomachine, comprising two coaxial annular walls, namely the inner wall and the outer wall, connected to each other by an annular chamber end wall, characterised in that at least one of said coaxial annular walls is a wall according to claim 1 .
5 . Turbomachine, including an annular combustion chamber according to the previous claim.