A method for manufacturing a flame tube for a turbomachine, the flame tube extending about an axis and comprising an annular radially internal wall and an annular radially external wall, connected to each other by an end wall or head wall, the internal wall, the external wall and the end wall defining an internal volume, at least one part of the said end wall forming a double wall comprising a first part and a second part connected to each other and spaced apart from each other so as to delimit a flow channel for a flow of cooling air opening into the said internal volume, the said flow channel comprising at least one air-inlet opening, the first and second parts of the double wall being connected by connecting zones or bridges extending into the flow channel for the cooling-air flow, the flame tube being manufactured by additive manufacturing.

A method for manufacturing a flame tube for a turbomachine, the flame tube extending about an axis and comprising an annular radially internal wall and an annular radially external wall, connected to each other by an end wall or head wall, the internal wall, the external wall and the end wall defining an internal volume, at least one part of the said end wall forming a double wall comprising a first part and a second part connected to each other and spaced apart from each other so as to delimit a flow channel for a flow of cooling air opening into the said internal volume, the said flow channel comprising at least one air-inlet opening, the first and second parts of the double wall being connected by connecting zones or bridges extending into the flow channel for the cooling-air flow, the flame tube being manufactured by additive manufacturing.

An assembly for a gas turbine having a combustion chamber, a swirler, a combustion zone in the combustion chamber, and an air feed. In a transition region from the air feed to the swirler that is flowed through by the air, a plenum is formed and the assembly adjoining the plenum has the swirler, the combustion chamber, and a cover closing the combustion chamber. The assembly has an air conduction channel designed to conduct part of the air flow flowing into the assembly into the combustion chamber, so that the air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone.

An assembly for a gas turbine having a combustion chamber, a swirler, a combustion zone in the combustion chamber, and an air feed. In a transition region from the air feed to the swirler that is flowed through by the air, a plenum is formed and the assembly adjoining the plenum has the swirler, the combustion chamber, and a cover closing the combustion chamber. The assembly has an air conduction channel designed to conduct part of the air flow flowing into the assembly into the combustion chamber, so that the air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone.

A combustor nozzle includes a nozzle main body extending along an axis. The nozzle main body includes a first fuel passage which extends along the axis and through which first fuel is configured to flow, a first fuel ejection passage which extends to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and is configured to eject the first fuel from the outer circumferential surface, an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air is configured to flow, and an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and is configured eject the purge air from the center of the distal end.

A combustor nozzle includes a nozzle main body extending along an axis. The nozzle main body includes a first fuel passage which extends along the axis and through which first fuel is configured to flow, a first fuel ejection passage which extends to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and is configured to eject the first fuel from the outer circumferential surface, an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air is configured to flow, and an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and is configured eject the purge air from the center of the distal end.

Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

A combustor component according to at least one embodiment of the present invention includes a cylindrical body which internally includes a combustion chamber, and includes a weld part where a plurality of through holes opening to the combustion chamber are formed, and a housing which is disposed on an outer circumferential side of the cylindrical body to cover a part of the weld part, and defines an acoustic damping space communicating with the combustion chamber via at least one of the through holes. The plurality of through holes in the weld part has a formation density which is higher in a first region of the weld part covered with the housing than in a second region of the weld part positioned outside the housing.

A combustor component according to at least one embodiment of the present invention includes a cylindrical body which internally includes a combustion chamber, and includes a weld part where a plurality of through holes opening to the combustion chamber are formed, and a housing which is disposed on an outer circumferential side of the cylindrical body to cover a part of the weld part, and defines an acoustic damping space communicating with the combustion chamber via at least one of the through holes. The plurality of through holes in the weld part has a formation density which is higher in a first region of the weld part covered with the housing than in a second region of the weld part positioned outside the housing.