ANNULAR COMBUSTION CHAMBER FOR A TURBOMACHINE

摘要

An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, comprising at the downstream end of one of its external or internal walls of revolution (48, 50) an annular flange (58) for fastening to a casing (62) of the turbomachine, the downstream end of the other wall of revolution of the chamber comprising means (66) which are spaced apart from another casing (40) of the turbomachine when cold and bear radially on this casing when hot.