Gas annular turbine combustion chamber with several injectors - includes injectors in tubular base domes for idling, with full gas take off injectors alternating circumferentially and domes being interconnected

The annular combustion chamber has axial walls (1,2), joined by a base (3), with several fuel injectors (13) through the base. The base has tubular dome cavities (16), opposite to the exhaust gas flow, domed to chamber front. Each tubular dome carries a pilot injector, providing fuel to an idling head, with full gas injectors alternating circumferentially, providing fuel to take off heads. The tubular domes (5) may be connected by tubes (16), ensuring flame propagation. The take off heads may carry premixing tubes between the tubular domes and base flame stabilising grilles. USE/ADVANTAGE - Aircraft gas turbines, with reduced temperature differentials, radial chamber dimensions and nitrous oxides. L'invention est relative à une chambre de combustion annulaire pour turbomachine, comportant des parois axiales (1, 2) réunies par un fond de chambre (3), et plusieurs injecteurs de carburant répartis en deux groupes d'injecteurs alternés alimentant respectivement des têtes de ralenti et des têtes de décollage. Des dômes tubulaires (5) s'étendent à partir du fond (3) vers l'avant de la chambre. Ces dômes (5) délimitent des cavités au fond desquelles sont disposées les têtes de ralenti.