Combustion chamber for a turbomachine including improved air inlets

A combustion chamber for a turbomachine, comprising:

• an annular end wall fitted with injection systems regularly distributed around a longitudinal axis of the combustion chamber, each of the injection systems has a central fuel emission axis;
• two coaxial annular walls, which are respectively internal and external, connected to one another by the end wall and including multiple air inlets formed on at least one of the two coaxial annular walls and the multiple air inlets open radially towards an outside relative to the longitudinal axis of the combustion chamber,
• wherein the multiple air inlets include inlets of a first type shaped such that an orthogonal projection of each of the air inlets of the first type in a corresponding projection plane, which passes through the central fuel emission axis of the injection system closest to the air inlet of the first type, and which is perpendicular to a corresponding axial plane passing jointly through the central fuel emission axis and through the longitudinal axis of the combustion chamber, has an upstream edge which is of convex shape when seen from downstream,
• wherein the air inlets of the first type include primary inlets formed around an upstream region of the combustion chamber, and
• wherein each of the injection systems is configured to emit a layer of blended fuel and air having a region of maximum fuel concentration located roughly on a truncated right circular cone centered on the central axis of the injection system, and having an apex located at an exit of the injection system, and the orthogonal projection of each of the primary inlets of the first type in the corresponding axial projection plane is intercepted by a corresponding straight line resulting from the intersection of the corresponding truncated cone with the corresponding axial projection plane.