Combustion chamber module for aircraft jet engines comprises combustion chamber, front end of whose external wall is attached to annular bracket with radial bars which fit into groove in wall of frame

摘要

The combustion chamber module comprises a combustion chamber the front end of whose external wall is attached to an annular bracket (17) with radial bars (36) which fit into a groove in the wall of a frame (16). An independent claim is included for turbomachines fitted with the module.