Turbine engine combustion module, in particular aircraft turbine engine combustion module, configured for the implementation of a constant-volume combustion, comprising at least two combustion chambers (12A, 12B), each chamber (12A, 12B, 12C) comprising a compressed gas inlet port and a flue gas exhaust port, and an ignition means triggering a combustion in the combustion chambers (12A, 12B, 12C), the chambers (12A, 12B, 12C) being arranged about an axis, the module comprising at least one conduit capable of connecting a first of the combustion chambers with at least one second of the combustion chambers to inject flue gases coming from the first combustion chamber in said second combustion chamber in order to trigger a combustion in said second combustion chamber, the module comprising a shutter (30, 82) for the opening/closing of the conduit capable of selectively enabling the passage of flue gases from the first combustion chamber, to said second combustion chamber, said turbine engine combustion module being characterised in that it further comprises respective common inlet /exhaust valves, synchronised and mounted rotarily about said axis to open and close the inlet /exhaust ports of the combustion chambers (12A, 12B, 12C), said valves (28, 30) cooperating with a radial opening (36, 38) which is formed in a wall shaped in a cylindrical section of the combustion chamber turned towards the axis, each corresponding inlet or exhaust rotary valve comprising a tubular element (40, 42), of diameter corresponding to said cylindrical section mounted coaxially rotating to said cylindrical section, said tubular element (40, 42) comprising a bore (44, 46) enabling the flow of inlet/exhaust gases, and at least one radial aperture (50, 52), arranged substantially in an axial plane of the radial opening (36, 38) of said port (16, 18), and which is capable of closing or releasing said radial opening (36, 38) during the rotation of said tubular element (40, 42) and in that at least one of the rotary valves comprises, on its periphery, a groove section which extends over an angular sector determined from the periphery of the rotary valve to form said conduit intended to connect a first of the combustion chambers (12A, 12B, 12C) and a second of the adjoining combustion chambers (12B, 12C, 12A) of said first chamber (12A, 12B, 12C), in an angular position of said rotary valve corresponding to a end of combustion in the first chamber (12A; 12B, 12C) prior to a discharge of the flue gases and an end-of-fill of the second chamber (12B, 12C, 12A) prior to the combustion, the rotary valve forming the shutter (30, 82) according to its angular position. the chambers (12A, 12B, 12C) being arranged about an axis, the module comprising at least one conduit capable of connecting a first of the combustion chambers with at least one second of the combustion chambers to inject flue gases coming from the first combustion chamber in said second combustion chamber in order to trigger a combustion in said second combustion chamber, the module comprising a shutter (30, 82) for the opening/closing of the conduit capable of selectively enabling the passage of flue gases from the first combustion chamber, to said second combustion chamber, said turbine engine combustion module being characterised in that it further comprises respective common inlet /exhaust valves, synchronised and mounted rotarily about said axis to open and close the inlet /exhaust ports of the combustion chambers (12A, 12B, 12C), said valves (28, 30) cooperating with a radial opening (36, 38) which is formed in a wall shaped in a cylindrical section of the combustion chamber turned towards the axis, each corresponding inlet or exhaust rotary valve comprising a tubular element (40, 42), of diameter corresponding to said cylindrical section mounted coaxially rotating to said cylindrical section, said tubular element (40, 42) comprising a bore (44, 46) enabling the flow of inlet/exhaust gases, and at least one radial aperture (50, 52), arranged substantially in an axial plane of the radial opening (36, 38) of said port (16, 18), and which is capable of closing or releasing said radial opening (36, 38) during the rotation of said tubular element (40, 42) and in that at least one of the rotary valves comprises, on its periphery, a groove section which extends over an angular sector determined from the periphery of the rotary valve to form said conduit intended to connect a first of the combustion chambers (12A, 12B, 12C) and a second of the adjoining combustion chambers (12B, 12C, 12A) of said first chamber (12A, 12B, 12C), in an angular position of said rotary valve corresponding to a end of combustion in the first chamber (12A; 12B, 12C) prior to a discharge of the flue gases and an end-of-fill of the second chamber (12B, 12C, 12A) prior to the combustion, the rotary valve forming the shutter (30, 82) according to its angular position.