Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements.

Abstract: The invention referring to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer arrangement for admixing a dilution air to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer is adapted to guide combustion gases in a hot gas flow path extending between the first combustion chamber. The second burner including a duct having an inlet at an upstream end adapted for connection to the first combustion chamber and an outlet at a downstream end adapted for connection to the second burner. The mixer includes at least one group of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution air to cool the hot flue gases leaving the first combustion chamber.

Abstract: An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimited by the burner wall, to a combustion chamber. In the mixing chamber the hot combustion gas is mixed with an injected fuel, where cooling air from the outside of the burner wall flows through effusion holes in the burner wall into an interior of the mixing chamber. The cooling air, on the outside of the burner wall, is deflected in a directed manner in its flow direction by means of deflection elements which are in a distributed arrangement.

Abstract: A reheat burner (1) includes a channel (2) with a lance (3) protruding thereinto to inject a fuel over an injection plane (4) perpendicular to a channel longitudinal axis (15). The channel (2) and lance (3) define a vortex generation zone (6) upstream of the injection plane (4) and a mixing zone (9) downstream of the injection plane (4) in the hot gas (G) direction. The mixing zone (9) includes a high speed area (16) with a constant cross section, and a diffusion area (17) with a flared cross section downstream of the high speed area (16) in the hot gas (G) direction.

Abstract: A reheat burner includes a channel with a lance projecting thereinto to inject a fuel over an injection plane perpendicular to a channel longitudinal axis. The channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas direction. The mixing zone has a cross section with diverging side walls in the hot gas direction. The diverging side walls define curved surfaces in the hot gas direction having a constant radius.

Abstract: The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles.

Abstract: An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052.

Abstract: The invention relates to a mixing arrangement for mixing a fuel with a stream of oxygen containing gas flowing along an axis in an axial channel, especially in the second combustor of a gas turbine with sequential combustion. The mixing is improved and the mixing length reduced by said mixing arrangement comprising an injector with at least one injector ring, which is passed by said stream of gas inside and outside.

Abstract: The combustion device includes a burner, a combustion chamber downstream of the burner, a lance projecting into the burner for fuel and air injection, and a plenum that at least partly houses the burner. The plenum is connected to the inside of the lance to supply an oxidiser to it.

Abstract: The burner (1) for a gas turbine includes a duct (2) housing a plurality of tetrahedron shaped vortex generators (3) and a lance (4) to inject a fuel to be combusted. Within the duct (2), a plurality of vortex generators (3) are provided with a plurality of holes (9) for injecting cooling air. The cooling holes (9) define passing through areas that are non-uniformly distributed on a top wall (11) of the vortex generators (3). A method for locally cooling a hot gases flow passing through a burner includes non-uniformly injecting cooling air from a vortex generator into the hot gas flow in the duct, which can reduce the occurrence of flashback in the burner.

Abstract: A reheat burner arrangement including a center body, an annular duct with a cross-section area, an intermediate fuel injection plane located along the center body and being actively connected to the cross section area of the annular duct, wherein the center body is located upstream of a combustion chamber, wherein the structure of the reheat burner arrangement is defined by various parameters and the structure of the reheat burner arrangement is defined by various dependencies.

Abstract: The disclosure relates to a burner such as for a secondary combustion chamber of a gas turbine with sequential combustion having a first and a second combustion chamber, with an injection device for introduction of at least one gaseous and/or liquid fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one gaseous fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. At least one nozzle has its outlet orifice downstream of a trailing edge of the streamlined body.

Abstract: The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device. The mixing and injection device includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies, each extending in a first transverse direction into the gas-flow channel. Each streamlined body has two lateral surfaces that are arranged essentially parallel to the main-flow direction, the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body. Each streamlined body has a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile.

Abstract: The invention discloses a method for operating a gas turbine with sequential combustion, which gas turbine includes a compressor, a first combustor with a first combustion chamber and first burners, which receives compressed air from the compressor, a second combustor with a second combustion chamber and second burners, which receives hot gas from the first combustor with a predetermined second combustor inlet temperature, and a turbine, which receives hot gas from the second combustor. The CO emission for part-load operation is reduced by reducing the second combustor inlet temperature for base-load operation of the gas turbine, and increasing the second combustor inlet temperature when decreasing the gas turbine load (RLGT) from base-load to part-load.

Abstract: A burner, such as for a secondary combustion chamber of a gas turbine with sequential combustion having first and second combustion chambers, includes an injection device for introducing at least one gaseous fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the gaseous fuel into the burner. The body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body. The body has two lateral surfaces substantially parallel to the main flow direction. At least one vortex generator is located on at least one lateral surface upstream of the at least one nozzle.

Abstract: The disclosure relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, wherein the at least one body is located in a first section of the burner with a first cross-sectional area at a leading edge of the at least one body with reference to a main flow direction prevailing in the burner, wherein downstream of said body a mixing zone is located with a second cross-sectional area, and at and/or downstream of said body the cross-sectional area is reduced, such that the first cross-sectional area is larger than the second cross-sectional area.

Abstract: The disclosure relates to a burner such as for a secondary combustion chamber of a gas turbine with sequential combustion having a first and a second combustion chamber, with an injection device for introduction of at least one gaseous and/or liquid fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one gaseous fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. At least one nozzle has its outlet orifice downstream of a trailing edge of the streamlined body.

Abstract: The disclosure relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, wherein the at least one body is located in a first section of the burner with a first cross-sectional area at a leading edge of the at least one body with reference to a main flow direction prevailing in the burner, wherein downstream of said body a mixing zone is located with a second cross-sectional area, and at and/or downstream of said body the cross-sectional area is reduced, such that the first cross-sectional area is larger than the second cross-sectional area.

Abstract: A burner, such as for a secondary combustion chamber of a gas turbine with sequential combustion having first and second combustion chambers, includes an injection device for introducing at least one gaseous fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the gaseous fuel into the burner. The body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body. The body has two lateral surfaces substantially parallel to the main flow direction. At least one vortex generator is located on at least one lateral surface upstream of the at least one nozzle.

Abstract: The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles.