The present invention relates to methods and systems for controlling a combustion reaction and the products thereof. One embodiment includes a combustion control system having an oxygenation stream substantially comprising oxygen and CO.sub.2 and having an oxygen to CO.sub.2 ratio, then mixing the oxygenation stream with a combustion fuel stream and combusting in a combustor to generate a combustion products stream having a temperature and a composition detected by a temperature sensor and an oxygen analyzer, respectively, the data from which are used to control the flow and composition of the oxygenation and combustion fuel streams. The system may also include a gas turbine with an expander and having a load and a load controller in a feedback arrangement.

The present invention relates to methods and systems for controlling a combustion reaction and the products thereof. One embodiment includes a combustion control system having an oxygenation stream substantially comprising oxygen and CO.sub.2 and having an oxygen to CO.sub.2 ratio, then mixing the oxygenation stream with a combustion fuel stream and combusting in a combustor to generate a combustion products stream having a temperature and a composition detected by a temperature sensor and an oxygen analyzer, respectively, the data from which are used to control the flow and composition of the oxygenation and combustion fuel streams. The system may also include a gas turbine with an expander and having a load and a load controller in a feedback arrangement.

A method for replacing a swirler (2) of a premixing or main burner of a burner arrangement (1), wherein the swirler (2) is connected to a distributor flange plate (5) of the burner arrangement (1) via a fuel gas feed pipe (3) and a fuel oil feed line (4) accommodated therein. The fuel gas feed line and the fuel oil feed line are severed to enable removal of the separated end portion of the fuel gas feed line. A sleeve is installed to replace the removed end portion.

A method for replacing a swirler (2) of a premixing or main burner of a burner arrangement (1), wherein the swirler (2) is connected to a distributor flange plate (5) of the burner arrangement (1) via a fuel gas feed pipe (3) and a fuel oil feed line (4) accommodated therein. The fuel gas feed line and the fuel oil feed line are severed to enable removal of the separated end portion of the fuel gas feed line. A sleeve is installed to replace the removed end portion.

In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

A premixer assembly for a combustor includes: at least one ring of premixers, each premixer having a central axis, an annular peripheral wall surrounding a centerbody, and at least one swirler disposed between the centerbody and the peripheral wall, wherein the peripheral wall defines an inlet area of the premixer; and a lip extending forward along the central axis from the peripheral wall, the lip extending at an oblique angle to the axis of symmetry.

A multi-tube combustor and a gas turbine having the same are provided. The multi-tube combustor includes a nozzle casing configured to receive compressed air from a compressor section and to receive fuel from outside, a liner coupled to the nozzle casing and defining a combustion chamber in which a mixture of fuel ejected from the nozzle casing and the compressed air is combusted, a transition piece connected to the liner and configured to supply the combustion gas generated in the combustion chamber defined by the liner to a turbine section, a plurality of fuel nozzles disposed in a nozzle tube provided inside the nozzle casing, each fuel nozzle having a cavity, a plurality of compressed air supply tubes connected to the plurality of fuel nozzles and configured to supply the compressed air to the plurality of fuel nozzles, a center body having a first end connected to a nozzle base of the nozzle casing, extended to enter the cavity of the fuel nozzle, and having a second end having a fuel ejection hole through which the fuel is ejected, and an on/off valve provided on the plurality of compressed air supply tubes to open and close the compressed air supply tubes. The fuel and the compressed air are mixed inside the plurality of fuel nozzles, and the plurality of fuel nozzles are divided into a plurality of fuel nozzle groups, and a mixture of the fuel and the compressed air is ejected from one or more selected fuel nozzle groups of the plurality of fuel nozzle groups according to a combustion load condition or during a ramp-up process.