Annular shielding for annular combustion chamber of e.g. aircraft turbojet engine, has openings permitting passage of injectors supported by chamber base and extended till free end of outer edge, such that edge is split between points

摘要

The shielding (10) has inner and outer fixation edges (10a, 10b) fixed on both sides of a base (11) of an annular combustion chamber of a turbomachine by fixation points. Openings (16) permit a passage of fuel injectors (14) that are supported by the base of the chamber. The openings are extended till a free end of the outer fixation edge (10b), such that the outer fixation edge is split between the fixation points. The openings define retaining brackets (17) that are extended in the direction of the base of the chamber.