Abstract: A constant volume combustion system for a turbomachine comprises a plurality of combustion chambers distributed annularly about an axis, each combustion chamber comprising an inlet orifice and an outlet orifice, a selective shut-off element movable in rotation relative to the combustion chambers, the selective shut-off element comprising a shroud facing the inlet and outlet orifices of the combustion chambers. The shroud including on a first annular portion at least one intake aperture intended to cooperate with the inlet orifice of each combustion chamber during the rotation of the selective shut-off element and on a second annular portion at least one exhaust aperture intended to cooperate with the outlet orifice of each combustion chamber during the rotation of the selective shut-off element. Each combustion chamber comprises a fuel injection device whose opening and closing are synchronized by the shut-off element.

Abstract: A turbine engine combustion chamber module including at least one constant-volume combustion chamber. The module includes, upstream of the at least one constant-volume combustion chamber, a precombustion chamber capable of producing hot combustion gases that supply the at least one constant-volume combustion chamber so as to allow the ignition thereof.

Abstract: A constant-volume combustion system is for a turbine engine. The system includes a plurality of combustion chambers regularly distributed around a longitudinal axis; a toroidal manifold including a radially oriented outlet for supplying compressed air, from a compressor, to each combustion chamber; a toroidal exhaust pipe including a radially oriented inlet for collecting the combustion gases from the combustion chambers, the combustion chambers being radially positioned between the outlet of the manifold and the inlet of the exhaust pipe; and a timing device for each chamber for drawing in compressed air from the outlet of the manifold and ejecting combustion gas towards the exhaust pipe.

Abstract: An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.

Abstract: The fixed vanes of a diffuser are set to an azimuth angle setting (?) with respect to the injectors of a combustion chamber so that the paths leading from the trailing edges pass through the gaps between injectors and more preferably mid-way between same, so that these portions of the flow, which may contain condensed water, do not affect the initiation of the combustion.

Abstract: An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.