DEMOUNTED COMBUSTION CHAMBER WITH IMPROVED AERODYNAMIC CHARACTERISTICS Russian patent published in 2011 - IPC F23R3/60 

FIELD: engines and pumps.

SUBSTANCE: combustion chamber of jet turbine engine includes outer annular wall, inner annular wall and rear wall of chamber and cowling. Rear wall is located between outer and inner walls and spraying devices are mounted on it. Cowling together with rear wall of chamber restricts annular cavity in which spraying devices are located. Cowling includes annular part called external cover and annular part called internal cover. Inner fasteners protruding inside the annular cavity are fixed in covers. Rear chamber wall includes the appropriate inner fasteners protruding inside annular cavity. Fasteners of covers are connected to fasteners of rear wall of the chamber and represent keys equally spaced in circumferential direction. Spraying devices include multiple atomisers. Each cover includes as many keys as there are atomisers; at that, keys are mixed in circumferential direction relative to atomisers.

EFFECT: simplifying the removal of combustion chamber during its repair.

10 cl, 3 dwg