Abstract: A burner for a combustion chamber of a gas turbine with a mixing and injection device, which includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies. Each streamlined body extends in a first transverse direction into the gas-flow channel, and has two lateral surfaces that are arranged essentially parallel to the main-flow direction. The lateral surfaces are joined to one another at their upstream and downstream sides to form leading and trailing edges of the body, respectively. At least one of the streamlined bodies includes a mixing structure and at least one fuel nozzle at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel. At least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.

Abstract: A burner for a combustion chamber of a gas turbine with a mixing and injection device, which includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies. Each streamlined body extends in a first transverse direction into the gas-flow channel, and has two lateral surfaces that are arranged essentially parallel to the main-flow direction. The lateral surfaces are joined to one another at their upstream and downstream sides to form leading and trailing edges of the body, respectively. At least one of the streamlined bodies includes a mixing structure and at least one fuel nozzle at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel. At least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.

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 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: 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 combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

Abstract: The invention relates to a damper for reducing the pulsations in a chamber of a gas turbine. The damper includes a resonator cavity and a neck in flow communication with the resonator cavity and the chamber. The neck includes a mouth to communicate with the chamber. The air flow inside the chamber flows across the mouth of the neck. The neck is so configured that the longitudinal axis of its mouth is angled 0-90° relative to the direction of the air flow inside the chamber. The damper of this invention may effectively alleviate the detrimental effect of the grazing flow and thus it enables the placement of the damper also at locations where strong grazing flows are present.

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: A method for operating a combustion device includes supplying a fuel and an oxidizer into the combustion device and burning them. According to the method, during at least a part of a transient operation, an additional fluid is supplied together with the fuel, and its amount is regulated to counteract combustion pulsations.

Abstract: A burner for a combustion chamber of a gas turbine with a mixing and injection device, which includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies. Each streamlined body extends in a first transverse direction into the gas-flow channel, and has two lateral surfaces that are arranged essentially parallel to the main-flow direction. The lateral surfaces are joined to one another at their upstream and downstream sides to form leading and trailing edges of the body, respectively. At least one of the streamlined bodies includes a mixing structure and at least one fuel nozzle at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel. At least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.

Abstract: A burner for a combustion chamber of a gas turbine with a mixing and injection device, which includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies. Each streamlined body extends in a first transverse direction into the gas-flow channel, and has two lateral surfaces that are arranged essentially parallel to the main-flow direction. The lateral surfaces are joined to one another at their upstream and downstream sides to form leading and trailing edges of the body, respectively. At least one of the streamlined bodies includes a mixing structure and at least one fuel nozzle at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel. At least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.

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: The disclosure concerns a nozzle for a gas turbine combustor, the nozzle comprising an inner channel, a swirl channel, a mixing zone and an outlet channel, wherein the nozzle extends from an inlet to an outlet, the swirl channel is disposed around the inner channel, the inner channel and the swirl channel extend from the inlet to the mixing zone, the mixing zone extends from the inner channel and the swirl channel to the outlet channel, and the outlet channel extends from the mixing zone to the outlet. A burner and a gas turbine comprising the nozzle are also described, along with a method of using the nozzle.

Abstract: An acoustic damping device is provided which includes at least one opening for a sealing gas to deflect a grazing gas flow away from the mouth of an acoustic damper.

Abstract: An exemplary method for switching over a combustion device from operation with a first premix fuel to a second premix fuel includes reducing and stopping a first premix fuel supply and then starting a second premix fuel supply. In an intermediate phase, after the first premix fuel supply stop and before the second premix fuel supply start, the combustion device is operated with one or more pilot fuels generating diffusion flames.

Abstract: The present invention relates to a gas turbine combustor comprising: a flow sleeve; a combustion liner located at least partially within the flow sleeve thereby creating a main passage between the flow sleeve and the combustor liner; a dome located forward of the flow sleeve and encompassing at least a part of the combustion liner, the dome having a substantially rounded head end thereby forming a turning passage between the liner and the head end; and a swirler wall aligned along a centerline of the combustor, the swirler wall projecting into the liner, wherein the swirler wall and the rounded head end are connected, wherein the connection forms an annular end face.

Abstract: An acoustic damper includes a neck and a damping volume. The neck has a mouth being in fluid connection with a chamber. The chamber is limited by an inner surface of at least one wall. The acoustic damper device includes a recess located between the mouth of the neck and the inner surface of the wall.

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: 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 combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

Abstract: A method and apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L).

Abstract: A premix burner is provided for a gas turbine, in the form of a double-cone burner, which has two partial cone shells which are arranged nested one inside the other, forming air inlet ducts between them, through which combustion air from the outside flows into a conical inner space of the premix burner. Linear rows of holes of injection openings, which extend transversely to the flow direction of the combustion air, are arranged on the outer walls of the air inlet ducts and through which a gaseous fuel is injected into the combustion air which flows past transversely to them. A method for reworking such premix burners is also provided.