An assembly for a turbomachine extending along an axis includes a combustion chamber having, at its downstream end, a downstream flange having a radially extending part. The assembly further includes a distributor disposed downstream of the combustion chamber and having a platform from which at least one vane extends radially. The platform includes an upstream flange extending radially and delimiting, with the radial part of the downstream flange disposed opposite it. An annular space for the circulation of cooling air opens into the combustion chamber at its radially internal end and has, at its radially external end, means of sealing attached to the distributor.

An assembly for a turbomachine extending along an axis includes a combustion chamber having, at its downstream end, a downstream flange having a radially extending part. The assembly further includes a distributor disposed downstream of the combustion chamber and having a platform from which at least one vane extends radially. The platform includes an upstream flange extending radially and delimiting, with the radial part of the downstream flange disposed opposite it. An annular space for the circulation of cooling air opens into the combustion chamber at its radially internal end and has, at its radially external end, means of sealing attached to the distributor.

This exit seal is for connecting an exit flange of a combustor and a shroud in a stator blade of a turbine. The exit seal is equipped with: a seal body that extends in a circumferential direction; and a lid member disposed at a circumferential end of the seal body. The seal body comprises one or more recessed sections that are recessed in a radial direction or in an axial direction and extend in the circumferential direction. At a position of the circumferential end of at least one recessed section among the one or more recessed sections, the lid member is disposed so as to overlap, in the axial direction and the radial direction, with a recessed space formed by the one recessed section.

A combustion cylinder mounting method, wherein a preparation step, a first contact maintenance step, a second contact maintenance step, and a combustion cylinder fixing step are executed. In the preparation step, a combustion cylinder mounting jig equipped with a spacer portion capable of maintaining a predetermined spacing between a first combustion cylinder and a second combustion cylinder adjacent to each other in the circumferential direction is prepared. In the first contact maintenance step, the spacer portion is brought into contact with the first combustion cylinder attached to the stationary portion of a casing. In the second contact maintenance step, the second combustion cylinder is brought into contact with the spacer portion. In the combustion cylinder fixing step, the second combustion cylinder is attached to the stationary portion while the first combustion cylinder and the second combustion cylinder are in contact with the spacer portion.

A combustion cylinder mounting method, wherein a preparation step, a first contact maintenance step, a second contact maintenance step, and a combustion cylinder fixing step are executed. In the preparation step, a combustion cylinder mounting jig equipped with a spacer portion capable of maintaining a predetermined spacing between a first combustion cylinder and a second combustion cylinder adjacent to each other in the circumferential direction is prepared. In the first contact maintenance step, the spacer portion is brought into contact with the first combustion cylinder attached to the stationary portion of a casing. In the second contact maintenance step, the second combustion cylinder is brought into contact with the spacer portion. In the combustion cylinder fixing step, the second combustion cylinder is attached to the stationary portion while the first combustion cylinder and the second combustion cylinder are in contact with the spacer portion.

To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. In a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor, the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle, and an interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.

A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.

A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.

A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.

A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.