Constant volume turbomachine combustion chamber

A combustion chamber of an aircraft turbomachine having a main axis and including:

• a body of revolution coaxial with the main axis in which a plurality of combustion tubes are formed, said combustion tubes extending mainly in the direction of the main axis of the body and being distributed in a ring about said main axis,
• a first perforated rotary disc which is mounted at a first axial end of the body and which is movable in rotation about the main axis to selectively open or close a first end of each of said combustion tubes, and
• a second perforated rotary disc which is mounted at a second axial end of the body and which is movable in rotation about the main axis to selectively open or close a second end of each of said combustion tubes,
• wherein the body includes a plurality of cooling segments which extend mainly in the direction of the main axis, which are distributed in a ring about said main axis and around the combustion tubes and are configured to cool a radially outer portion of the body, and
• wherein each cooling segment is open at each axial end of the body and is passed through by a compressed air flow,
• wherein each rotary disc is coaxial with the main axis, includes a series of lumens intended to face one end of each combustion tube and in a selective manner, and includes a series of orifices intended to face one end of each cooling segment in a selective manner,
• wherein each rotary disc is configured to selectively open or close a corresponding end of the cooling segments when the orifices are facing an associated axial end of the cooling segments.