FIELD: engines and pumps.
SUBSTANCE: combustion chamber for, in fact, gas turbine engine features circular shape and comprises inner circular wall, outer circular wall and the chamber circular end wall extending along the axis. The chamber circular end wall extends radially between the inner and outer circular walls. The chamber circular end wall has fuel injector seat hole. The latter is centred in circular line that confines the first end of the chamber end wall extending radially between circular line and inner circular wall and the second end wall extending radially between circular line and outer circular wall. Said combustion chamber has multiple first channels in the combustion chamber end wall first part and multiple second channels in the second part of its end wall. Said first and second channels are inclined to the chamber end wall and extend tangentially. First channels are arranged to allow air flow around the chamber axis in the first direction while second channels allow air flow around said axis in the second direction opposite the first one.
EFFECT: higher strength, lower costs.
11 cl, 6 dwg
