Combustion chamber for an aircraft turbine engine, comprising: - an annular chamber-end structure, and two coaxial annular walls (32, 34) connected together by the annular chamber-end structure and centred with respect to a longitudinal axis of the combustion chamber, so that the annular chamber-end structure and the two coaxial annular walls (32, 34) delimit an interior volume of the combustion chamber; - main passages formed through the annular chamber-end structure; - an annular row of main injection systems mounted respectively in the main passages, each main injection system comprising a respective main fuel-injection nozzle defining a respective injection axis, and at least one respective air-inlet swirler (56, 58), for delivering, in the interior volume of the combustion chamber, a respective sheet of an air/fuel mixture, centred on the respective injection axis and comprising a respective central recirculation region, and a respective corner recirculating region extending annularly around the respective central recirculation region; - secondary injection systems each configured for injecting an additional flow of air and fuel directly into the respective corner recirculation region of the sheet of air-fuel mixture delivered by a corresponding main injection system, each secondary injection system comprising at least one secondary injection device configured for supplying at least part of the fuel of the corresponding additional flow of air and fuel and at least part of the air of the corresponding additional flow of air and fuel, through a corresponding secondary injection region of the annular chamber-end structure separated from the main passage through which the corresponding main injection system is mounted, wherein each secondary injection device includes a respective secondary fuel-injection nozzle, mounted in a corresponding secondary passage formed through the corresponding secondary injection region, in the annular chamber-end structure, to supply said at least part of the fuel of the corresponding additional flow of air and fuel, characterized in that each secondary injection device further includes a respective annular set of air-inlet orifices formed in the corresponding secondary injection region in the annular chamber-end structure, distributed around said corresponding secondary passage, and emerging in the interior volume of the combustion chamber, so as to supply said at least part of the air of the corresponding additional flow of air and fuel. - an annular chamber-end structure, and two coaxial annular walls (32, 34) connected together by the annular chamber-end structure and centred with respect to a longitudinal axis of the combustion chamber, so that the annular chamber-end structure and the two coaxial annular walls (32, 34) delimit an interior volume of the combustion chamber; - main passages formed through the annular chamber-end structure; - an annular row of main injection systems mounted respectively in the main passages, each main injection system comprising a respective main fuel-injection nozzle defining a respective injection axis, and at least one respective air-inlet swirler (56, 58), for delivering, in the interior volume of the combustion chamber, a respective sheet of an air/fuel mixture, centred on the respective injection axis and comprising a respective central recirculation region, and a respective corner recirculating region extending annularly around the respective central recirculation region; - secondary injection systems each configured for injecting an additional flow of air and fuel directly into the respective corner recirculation region of the sheet of air-fuel mixture delivered by a corresponding main injection system, each secondary injection system comprising at least one secondary injection device configured for supplying at least part of the fuel of the corresponding additional flow of air and fuel and at least part of the air of the corresponding additional flow of air and fuel, through a corresponding secondary injection region of the annular chamber-end structure separated from the main passage through which the corresponding main injection system is mounted,