Constant-volume combustion (cvc) chamber for an aircraft turbine engine including an intake/exhaust valve having a spherical plug

A constant-volume combustion chamber for an aircraft turbine engine, the combustion chamber comprising:

• a compressed gas intake valve configured to adopt an open position and a closed position, in the closed position blocking intake of compressed gas into the combustion chamber;
• and
• a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the combustion chamber;
• wherein at least one of the intake and exhaust valves comprises a spherical plug including:
• an inner spherical body traversed by a gas passage, and
• an outer spherical body housing the inner spherical body and including two mutually distant orifices,
• wherein the inner and outer spherical bodies, of which at least one acts as the spherical plug, are rotatably mounted in relation to each other, and the two orifices of the outer spherical body form in conjunction with the gas passage a first diaphragm at a first end of the gas passage and a second diaphragm at a second end of the gas passage,
• wherein the spherical plug of the exhaust valve includes a gas passage, and the combustion chamber enables, after a gas exhaust phase resulting in closure of the exhaust valve, recirculation of combusted gases trapped in the gas passage,
• wherein the exhaust valve includes a body forming a seat for the spherical plug, the body including a passage passing through the body,
• wherein the combustion chamber further comprises a conduit connected to the passage and to another combustion chamber, and
• wherein the spherical plug of the exhaust valve is designed to place the exhaust valve in an EGR position in which the gas passage communicates with the passage in order to enable the combusted gases trapped in the gas passage to be reinjected in the passage towards the another combustion chamber via the conduit.