annular wall of turbomachine combustion chamber, turbomachine combustion chamber, and turbomachine.

摘要

turbocharger combustion chamber annular wall, comprising between a cold side (16a, 18a) and a warm side (16b, 18b), a plurality of air inlet holes (30) distributed on at least one circumferential row to allow air circulating from the cold side penetrates the hot side, these air inlet holes creating around them high thermal gradient zones, and a plurality of cooling holes (32) to allow air circulating from the cold side to penetrate into the hot side. hot side in order to form a cooling air film along the annular wall, the annular wall further comprising, in the high thermal gradient zones, multi-perforation holes (36) angled at an angle of greater than 90 °, this angle at being taken between an input geometrical axis a and an output geometrical axis as those of the multi-bore hole, the multi-bore exit geometrical axis is inclined from an angle ¿3 to a standard n to the annular wall through which said angled multipuncture holes are drilled in a so-called direction of rotation at most perpendicular to the axial direction d of flue gas flow.