A combustion chamber for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine. The combustion chamber includes a radially outer annular shroud, a radially inner annular shroud coaxial with the radially outer shroud, and an end wall connecting the radially outer shroud and the radially inner shroud. The combustion chamber further includes a first annular sealing member coaxial with said radially inner and outer shrouds. The first annular sealing member is radially interposed between the end wall and the radially outer shroud.