Annular combustion chamber of a turbomachine, in particular of an aircraft, comprising two coaxial walls of revolution (14, 16) extending one inside the other and connected at their upstream ends by an annular wall chamber bottom, and joined at their downstream ends to annular fixing flanges (20, 24), said walls of revolution being made of a first material and said flanges being made of a second material different from said first material, characterized in that that it further comprises, in the annular zone of junction of at least one of said walls with the corresponding flange, an annular row of channels oriented parallel to this wall in this zone so that a film of gas penetrates into the chamber for the cooling of this junction zone.
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