FIELD: engines and pumps.
SUBSTANCE: annular wall for an annular turbine engine combustion chamber includes at least one annular row of cooling air inlets, which comprises two types of holes of different area of cross-section, specifically holes with larger cross-section area and holes with smaller area of cross section, and multi-perforation for cooling of said wall. Multi-perforation is formed by micro-perforations, cross-section area of which is smaller than area of each of said cooling air inlets, and distributed in form of annular row upstream and annular row downstream, formed on upstream side and downstream side from row of cooling air inlets, and at least one intermediate annular row, interrupted by said cooling air inlets. For each of said cooling air inlets, geometrical ratio is determined as quotient of maximum distance between any two points on edge of said hole, measured in direction parallel to central axis of wall at maximum distance between any two points on edge of said hole, measured in direction perpendicular to central axis of wall. Geometric ratio for cooling air inlets with larger cross-section area is greater than or equal to 1. Geometric ratio for cooling air inlets with smaller cross-section area is greater than geometrical ratio for cooling air inlets with larger cross-section area.
EFFECT: invention improves cooling perforation around cooling orifices using simple, cheap and effective means.
7 cl, 3 dwg
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