A combined-cycle power plant comprises a gas turbine engine for generating exhaust gas, an electric generator driven by the gas turbine engine, a steam generator receiving the exhaust gas to heat water and generate steam, and a duct burner system configured to heat exhaust gas in the steam generator before generating the steam and that comprises a source of hydrogen fuel, a fuel distribution manifold to distribute the hydrogen fuel in a duct of the steam generator, and an igniter to initiate combustion of the hydrogen fuel in the exhaust gas. A method for heating exhaust gas in a steam generator for a combined-cycle power plant comprises directing combustion gas of a gas turbine engine into a duct, introducing hydrogen fuel into the duct, combusting the hydrogen fuel and the combustion gas to generate heated gas, and heating water in the duct with the heated gas to generate steam.

A combined-cycle power plant comprises a gas turbine engine for generating exhaust gas, an electric generator driven by the gas turbine engine, a steam generator receiving the exhaust gas to heat water and generate steam, and a duct burner system configured to heat exhaust gas in the steam generator before generating the steam and that comprises a source of hydrogen fuel, a fuel distribution manifold to distribute the hydrogen fuel in a duct of the steam generator, and an igniter to initiate combustion of the hydrogen fuel in the exhaust gas. A method for heating exhaust gas in a steam generator for a combined-cycle power plant comprises directing combustion gas of a gas turbine engine into a duct, introducing hydrogen fuel into the duct, combusting the hydrogen fuel and the combustion gas to generate heated gas, and heating water in the duct with the heated gas to generate steam.

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 reheat assembly for gas turbine engine including a jetpipe casing having a reheat core section configured to flow air from inlet to outlet; and reheat bypass section configured to bypass air from inlet to outlet, wherein the reheat core section and the reheat bypass section are radially separated by support duct within the jetpipe casing; reheat arrangement including a radially extending flameholder and a core fuel injection port, wherein: the flameholder, mounted to the jetpipe casing, extends through the reheat bypass section and partly into the reheat core section; the flameholder is configured to form a wake-stabilised region within the core flow of air and the bypass flow of air downstream of the flameholder; and the core fuel injection port is: circumferentially aligned with the flameholder upstream of the wake-stabilised region, and configured to discharge fuel into the reheat core section for mixing with the core flow of air.

A reheat assembly for gas turbine engine including a jetpipe casing having a reheat core section configured to flow air from inlet to outlet; and reheat bypass section configured to bypass air from inlet to outlet, wherein the reheat core section and the reheat bypass section are radially separated by support duct within the jetpipe casing; reheat arrangement including a radially extending flameholder and a core fuel injection port, wherein: the flameholder, mounted to the jetpipe casing, extends through the reheat bypass section and partly into the reheat core section; the flameholder is configured to form a wake-stabilised region within the core flow of air and the bypass flow of air downstream of the flameholder; and the core fuel injection port is: circumferentially aligned with the flameholder upstream of the wake-stabilised region, and configured to discharge fuel into the reheat core section for mixing with the core flow of air.

A reheat assembly for a gas turbine engine includes: a jetpipe casing including: a reheat core section configured to convey a core flow of air from a reheat core inlet to a reheat core outlet; and a reheat bypass section configured to convey a bypass flow of air from a reheat bypass inlet to a reheat bypass outlet radially outward of the reheat core section, wherein the reheat core and reheat bypass sections are radially separated at the reheat core and reheat bypass inlets by a support duct within the jetpipe casing; a reheat arrangement including a radially extending flameholder and a plurality of fuel injection ports including a plurality of core fuel injection ports, wherein: the flameholder is configured to promote a formation of a core flow wake-stabilised region within the core flow of air downstream of the flameholder; and each of the plurality of core fuel injection ports are: circumferentially aligned with the flameholder upstream of the core flow wake-stabilised region, configured to discharge a respective flow of fuel into the reheat core section for mixing with the core flow of air, and offset with respect to one another along a radial direction of the jetpipe casing.

The subject matter of this specification can be embodied in, among other things, a fuel delivery component, a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure as a first loop.

A combustion device burns fuel ammonia with combustion air in a combustion chamber, and includes: a combustor liner which forms the combustion chamber; a burner which is installed at one end of the combustor liner; a deflection member which is provided on a downstream side of the combustor liner in a flow direction of a combustion gas, and is configured to deflect the flow direction of the combustion gas; and at least one ammonia injection hole which is provided between the burner and an outlet of the deflection member and is configured to supply the fuel ammonia into the combustion chamber.

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.