Annular wall of a combustion chamber with optimised cooling

An annular turbine engine combustion chamber wall comprising, between a cold side and a hot side:

• a plurality of air admission orifices distributed along at least one circumferential row to enable an air flowing on said cold side to penetrate to said hot side;
• and
• a plurality of cooling orifices to enable the air flowing on said cold side to penetrate to said hot side in order to form a film of cooling air along said annular wall, said cooling orifices being distributed in a plurality of circumferential rows that are axially spaced apart from one another, and axes of each of said cooling orifices being inclined in an axial flow direction of a combustion gas at an angle of inclination θ1 relative to a normal to said annular turbine engine combustion chamber wall;
• and
• in zones around a circumference of each of said plurality of air admission orifices, multi-perforation holes having respective bends of an angle α equal or greater than 90° , said angle α being measured between an inlet axis and an outlet axis of each of said multi-perforation hole, each said outlet axis of said multi-perforation holes being inclined at an angle θ3 relative to said normal to said annular turbine engine combustion chamber wall through which said multi-perforation holes with bends of an angle β lying in a range of 50° to 90° to said axial flow direction of the combustion gas wherein the multi-perforation holes and the cooling orifices alternate around at least a portion of a circumference of said plurality of air admission orifices.