Annular combustion chamber for turbine engine e.g. turbojet engine, of aircraft, has chamber base providing fixing edge fixed at annular wall, and air pipe flange provided with base and projecting toward downstream from base

摘要

The chamber (102) has a chamber base (8) providing a fixing edge (8a) fixed at an annular wall (16), where the wall is fixed at a fixation edge of the chamber by bolts (20, 22). The chamber defines a slot (130), between an upstream part of the wall and an air pipe flange (128), for passing a cooling air film (132) of the wall. The air pipe flange is provided with the base and projects toward a downstream from the base. The wall has annular perforations (142) opened in the slot, where the perforations and openings (140) of supply air are arranged in staggered rows.