Abstract: The present invention generally relates to a sequential combustor for a gas turbine having second and/or subsequent stages of a re-heat, sequential or axially-staged combustion system. A variation in Mach number along the flow path can be used to control static temperature variation, which in turn influences the progress of auto-ignition reactions that eventually lead to the onset of combustion.

Abstract: The invention relates to a can-combustor for a can-annular combustor arrangement in a gas turbine. The can combustor includes an essentially cylindrical casing with an axially upstream front panel and an axially downstream outlet end. The can combustor further includes a number of premixed burners, extending in an upstream direction from said front panel and having a burner exit, supported by this front panel, for supplying a fuel/air mixture into a combustion zone inside the casing. Up to four premixed burners are attached to the front panel in a substantially annular array. Each burner has a conical swirl generator and a mixing tube to induce a swirl flow of said fuel/air mixture.

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: The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

Abstract: The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

Abstract: The present invention generally relates to a sequential combustor for a gas turbine having second and/or subsequent stages of a re-heat, sequential or axially-staged combustion system. A variation in Mach number along the flow path can be used to control static temperature variation, which in turn influences the progress of auto-ignition reactions that eventually lead to the onset of combustion.

Abstract: The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Abstract: The invention relates to a premix burner of the multi-cone type for a gas turbine that includes a plurality of shells which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. The flame front of such a burner is stabilized by providing a virtual common cone with a cone angle, which varies in axial direction.

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: This invention relates to a premix burner for operating a heat generator, the burner at least having a swirl generator, a mixing section downstream of the swirl generator and a transition piece for transferring the swirl flow from the swirl generator into the mixing section. The invention further refers to a transition piece for such a premix burner. The transition piece includes an inlet, connected to the swirl generator, an outlet, connected to the mixing tube, and a continuing flow limiting interior contour between said inlet and said outlet, wherein at least in an inlet section said interior contour is curved radially inwards towards the inner diameter of the mixing tube and wherein at the outlet the interior contour is flush with an interior flow limiting contour of the mixing tube.

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: 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: 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: 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 method is provided for determining the approach of the lean blow off (LBO) of a gas turbine engine having at least one combustion chamber into which a fuel is supplied and burnt generating a flame. The method includes determining a value indicative of the gas temperature in recirculation areas adjacent to the flame, and identifying the lean blow off (LBO) approach on the basis of this value. A device for determining the approach of the lean blow off (LBO) is also disclosed.

Abstract: The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

Abstract: The invention relates to a can-combustor for a can-annular combustor arrangement in a gas turbine. The can combustor includes an essentially cylindrical casing with an axially upstream front panel and an axially downstream outlet end. The can combustor further includes a number of premixed burners, extending in an upstream direction from said front panel and having a burner exit, supported by this front panel, for supplying a fuel/air mixture into a combustion zone inside the casing. Up to four premixed burners are attached to the front panel in a substantially annular array. Each burner has a conical swirl generator and a mixing tube to induce a swirl flow of said fuel/air mixture.

Abstract: The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Abstract: This invention relates to a premix burner for operating a heat generator, the burner at least having a swirl generator, a mixing section downstream of the swirl generator and a transition piece for transferring the swirl flow from the swirl generator into the mixing section. The invention further refers to a transition piece for such a premix burner. The transition piece includes an inlet, connected to the swirl generator, an outlet, connected to the mixing tube, and a continuing flow limiting interior contour between said inlet and said outlet, wherein at least in an inlet section said interior contour is curved radially inwards towards the inner diameter of the mixing tube and wherein at the outlet the interior contour is flush with an interior flow limiting contour of the mixing tube.

Abstract: The invention relates to a premix burner of the multi-cone type for a gas turbine that includes a plurality of shells which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. The flame front of such a burner is stabilized by providing a virtual common cone with a cone angle, which varies in axial direction.