Abstract: An annular combustor includes an inner liner shell and an outer liner shell defining an interior volume through which combustion gases flow in a gas flow direction from a forward end to an aft end. A cooling shroud is attached radially outward of the inner liner shell, forming a cooling passage between the inner liner shell and the cooling shroud. The cooling passage directs air in an air flow direction opposite to the gas flow direction. The cooling shroud is assembled from circumferentially adjoined cooling shroud segments, and the distance between the cooling shroud segments and the inner liner shell is greater at the forward end than at the aft end. Fastening elements are distributed across an axial length of the cooling shroud segments in circumferentially staggered rows. Each forwardmost fastening element is disposed immediately adjacent to a curved portion at the forward end of each respective cooling shroud segment to reduce vibration.

Abstract: An annular combustor includes an inner liner shell and an outer liner shell defining an interior volume through which combustion gases flow in a gas flow direction from a forward end to an aft end. A cooling shroud is attached radially outward of the inner liner shell, forming a cooling passage between the inner liner shell and the cooling shroud. The cooling passage directs air in an air flow direction opposite to the gas flow direction. The cooling shroud is assembled from circumferentially adjoined cooling shroud segments, and the distance between the cooling shroud segments and the inner liner shell is greater at the forward end than at the aft end. Fastening elements are distributed across an axial length of the cooling shroud segments in circumferentially staggered rows. Each forwardmost fastening element is disposed immediately adjacent to a curved portion at the forward end of each respective cooling shroud segment to reduce vibration.

Abstract: A combustor arrangement includes a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to the front panel through an elongated mixing zone in an axially moveable fashion by a sealed sliding joint. A wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame is achieved by positioning the sealed sliding joint upstream of the mixing zone.

Abstract: The burner of a gas turbine includes two or more part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein. A lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber is also provided. A portion of the nozzle facing the cone shaped chamber is divergent in shape. A diffuser angle (?) between the wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5°. A diverging portion of the nozzle has a diffuser length to nozzle diameter ratio comprised between 2-6. The nozzle diameter is the smaller diameter of the diverging portion.

Abstract: A combustor for a gas turbine that includes a front panel, an elongated sleeve with first end and second ends and a burner mounted in the sleeve. The second end of the sleeve seallessly mounted on the front panel. The sleeve and burner are configured to enable slidable mounted of the burner in the sleeve.

Abstract: The invention relates to a combustor arrangement that includes a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to said front panel though an elongated mixing zone in an axially moveable fashion by means of a sealed sliding joint. A wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame is achieved by positioning said sealed sliding joint upstream of said mixing zone.

Abstract: The burner of a gas turbine includes two or more part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein. A lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber is also provided. A portion of the nozzle facing the cone shaped chamber is divergent in shape. A diffuser angle (?) between the wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5°. A diverging portion of the nozzle has a diffuser length to nozzle diameter ratio comprised between 2-6. The nozzle diameter is the smaller diameter of the diverging portion.

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber (30), an ignition device (10), a fuel supply (60) and an air supply (70), and the ignition device (10) consisting of an ignition space (50) and of an ignitor (51) arranged in the ignition space (50), the fuel supply (60) and the air supply (70) discharging into the ignition space (50), and the ignition space (50) being connected to the combustion chamber (30) via a flame tube (40), prior to the ignition of the combustion chamber (30), an overall fuel/air mixture ratio &PHgr;overall=1/&lgr;overall greater than 1, with &lgr;overall being the overall air ratio, is set in the flame tube (40) of the ignition device (10).

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber (30), an ignition device (10), a fuel supply (60) and an air supply (70), and the ignition device (10) consisting of an ignition space (50) and of an ignitor (51) arranged in the ignition space (50), the fuel supply (60) and the air supply (70) discharging into the ignition space (50), and the ignition space (50) being connected to the combustion chamber (30) via a flame tube (40), prior to the ignition of the combustion chamber (30), an overall fuel/air mixture ratio &PHgr;overall=1/&lgr;overall greater than 1, with &lgr;overall being the overall air ratio, is set in the flame tube (40) of the ignition device (10).

Abstract: In a method for operating a premix burner a water quantity is introduced into the burner and/or the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method in particular should also be used if a burner is operated in the actual sense dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable; such parameters are then kept below a permissible upper limit.

Abstract: In a method of operating a gas turbine, in which a gaseous fuel is burned in a combustion chamber and the hot combustion gases which are produced in the process are directed through the gas turbine, and in which method the gaseous fuel is fed to the combustion chamber via a plurality of controllable burners, working in parallel and arranged on one or more concentric, essentially circular rings, and is sprayed into the combustion chamber via fuel holes, high safety and availability within various operating ranges is achieved in a simple manner owing to the fact that the burners are divided into at least two groups (40-42) of burners, these groups in each case include the burners of one of the rings, and these groups are individually activated as a function of the operating state of the gas turbine.

Abstract: In a method of operating a gas turbine, in which a gaseous fuel is burned in a combustion chamber and the hot combustion gases which are produced in the process are directed through the gas turbine, and in which method the gaseous fuel is fed to the combustion chamber via a plurality of controllable burners, working in parallel and arranged on one or more concentric, essentially circular rings, and is sprayed into the combustion chamber via fuel holes, high safety and availability within various operating ranges is achieved in a simple manner owing to the fact that the burners are divided into at least two groups (40-42) of burners, these groups in each case comprise the burners of one of the rings, and these groups are individually activated as a function of the operating state of the gas turbine.

Abstract: A burner arrangement (20) for a gas turbine comprises an interior space (22) enclosed by a casing (23), in which interior space (22) at least one burner (21) is arranged, and into which interior space (22) in each case a jet (26, 27) of a gaseous medium, in particular air, is sprayed through at least two nozzle openings (24, 25) against the direction of flow of the burner (21) and along the inner wall (23a) of the casing (23) which jets (26, 27), guided by the inner wall (23a), meet one another from opposite directions and combine to form a secondary flow (28) flowing off perpendicularly from the inner wall (23a). In such a burner arrangement, the flow is stabilized and evened out by virtue of the fact that, to establish the impingement point of the jets (26, 27), a dividing plate (29) arranged in the flow path of the jets (26, 27) and disposed essentially perpendicularly to the inner wall (23a) is provided.

Abstract: In a gas-operated premixing burner for the combustion chamber of a gas turbine, the fuel injected within a premixing space (21) by means of a plurality of nozzles (17) is intensively mixed with the combustion air prior to ignition. The nozzles are arranged around a burner axis (10). In order to influence the fuel profile at outlet from the burner in a specific manner, the fuel concentration in the region of the burner axis is kept greater than the average fuel concentration at the burner outlet plane (22). For this purpose, additional burner nozzles (23) are provided in the region of the burner axis (10). The additional burner nozzles (23) can be supplied via a separate fuel conduit (24).