A fuel nozzle includes a shroud; an injection cylinder surrounded by the shroud and configured to supply fuel to a combustion chamber; a swirler disposed between the injection cylinder and the shroud; and a porous disk disposed downstream of the swirler to surround an outer peripheral surface of the injection cylinder in order to prevent a flashback phenomenon occurring due to a reduction in pressure around the swirler. The porous disk includes a disk body to block a flame produced in the combustion chamber, and a plurality of flow holes are formed in the disk body through which the fuel flows. It is possible to prevent flashback by installing the porous disk downstream of the swirler, and to impart linearity and a swirling effect to the fuel passing through the fuel nozzle by forming variously configured flow holes in the porous disk.

An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.

An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.

A burner assembly for a combustor includes: a plurality of first nozzles arranged in a circumferential direction of the combustor; a plurality of first burner cylinders accommodating the respective first nozzles; and a middle-flow-passage forming portion which is connected to a downstream end of the plurality of first burner cylinders and which forms a middle flow passage through which a combustion chamber of the combustor is in communication with an interior space of each of the plurality of first burner cylinders. The middle-flow-passage forming portion includes an inner peripheral wall disposed on a radially inner side of the combustor and formed such that a distance from a center axis of the combustor to the inner peripheral wall is uneven with respect to the circumferential direction.

A burner assembly for a combustor includes: a plurality of first nozzles arranged in a circumferential direction of the combustor; a plurality of first burner cylinders accommodating the respective first nozzles; and a middle-flow-passage forming portion which is connected to a downstream end of the plurality of first burner cylinders and which forms a middle flow passage through which a combustion chamber of the combustor is in communication with an interior space of each of the plurality of first burner cylinders. The middle-flow-passage forming portion includes an inner peripheral wall disposed on a radially inner side of the combustor and formed such that a distance from a center axis of the combustor to the inner peripheral wall is uneven with respect to the circumferential direction.

A burner designed to be fitted in a combustion chamber, the burner including: a central nozzle configured to have an oxidizer and fuel supply; several peripheral nozzles configured to have an oxidizer and fuel supply and which each have at least one upstream fuel injector in order to pre-mix the fuel and the oxidizer in the nozzle; at least one oxidizer input connected to the said central and/or peripheral nozzles; wherein peripheral nozzles each have a flame stabilizer located at the end of the peripheral nozzle designed to exit into the combustion chamber, as well as a tip injector to inject fuel at the end of the peripheral nozzle.

A reheat assembly for a gas turbine engine includes; a jetpipe casing defining a reheat core section configured to duct a core flow of air and a reheat bypass section configured to duct a bypass flow of air. The reheat bypass section is disposed radially outward of the reheat core section, and the reheat core section and the reheat bypass section are at least partially separated by a support duct. An integrated flameholder is mounted to the jetpipe casing, and a fuel pipe is configured to convey fuel to the integrated flameholder. The integrated flameholder includes a flameholder body extending radially inward from the jetpipe casing through the reheat bypass section and into the reheat core section to promote a wake-stabilised region downstream of the body; and an integrated atomiser configured to atomise fuel provided to the integrated flameholder and to discharge the atomised fuel into the wake stabilised region.

A reheat assembly for a gas turbine engine includes; a jetpipe casing defining a reheat core section configured to duct a core flow of air and a reheat bypass section configured to duct a bypass flow of air. The reheat bypass section is disposed radially outward of the reheat core section, and the reheat core section and the reheat bypass section are at least partially separated by a support duct. An integrated flameholder is mounted to the jetpipe casing, and a fuel pipe is configured to convey fuel to the integrated flameholder. The integrated flameholder includes a flameholder body extending radially inward from the jetpipe casing through the reheat bypass section and into the reheat core section to promote a wake-stabilised region downstream of the body; and an integrated atomiser configured to atomise fuel provided to the integrated flameholder and to discharge the atomised fuel into the wake stabilised region.

A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.

A propulsion system is provided, wherein the propulsion system includes an afterburner assembly. The afterburner assembly including: an exhaust section and a fuel injector assembly that is operable to inject fuel in the exhaust section. The fuel injector assembly includes a plurality of fuel injection members. The plurality of fuel injection members defines a hot zone and a cold zone. The cold zone is positioned to provide a noise insulation barrier for the hot zone.