Annular combustion chamber for e.g. turbojet engine of aircraft, has fairing including annular ends fixed by bolts by aligning ends with annular ends of outer and inner walls of chamber, where aligned ends have indentations/corrugations

摘要

The chamber (10) has inner and outer cylindrical walls radially arranged with respect to an axis of a turbomachine e.g. turbojet engine, and fixed by bolts at their annular upstream ends (46, 48) on annular inner and outer flanges (54, 56) of an annular chamber bottom. An annular fairing is extended towards the upstream from the bottom. The fairing has outer and inner downstream annular ends (52, 50) fixed by the bolts on the respective flanges, by axially aligning the ends with the ends (46, 48) of the outer and inner walls, where the aligned ends have complementary indentations/corrugations.