Abstract: A combustion chamber including a body with a fuel supply duct for supplying a fuel into the body and a carrier air supply duct for supplying air into the body. An adjusting system adjusts the carrier air mass flow supplied into the body according to the features of the fuel.

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 method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating the nitrogen (N2) percentage content as the complement to 100 of the measured percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.

Abstract: The method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating the nitrogen (N2) percentage content as the complement to 100 of the measured percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.

Abstract: The method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating the nitrogen (N2) percentage content as the complement to 100 of the measured percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.

Abstract: The present disclosure refers to a method for operating a gas turbine with a sequential combustor arrangement having: a first burner, a first combustion chamber, and a second combustor. A fuel gas is separated into a rich fuel having a concentration of higher hydrocarbons which is higher than the concentration of higher hydrocarbons of the fuel gas supplied to the plant, and a lean fuel having a concentration of higher hydrocarbons which is lower than the concentration of higher hydrocarbons of the fuel gas. A first fuel and a second fuel mixed from at least one of the rich fuel, the lean fuel, and the fuel gas are fed to different combustors of the gas turbine.

Abstract: The present disclosure generally relates to the field of combustion technology related to gas turbines. For example, the present disclosure refers to a system and a method for operating a combustion device. Advantageously, required measurements may be effected fast enough to ensure an optimum control of parameter w, defined as a ratio between NOx water mass and fuel oil flows, the measurements being based not only on process variables but, most importantly, on NOx levels.

Abstract: A gas turbine and method for operating a gas turbine, includes a compressor, a combustor, a turbine and a cooling air cooling system having at least a first cooling air line going from a first bleed of the compressor to the turbine, and at least one second cooling air line at a downstream position of the compressor relative to the first cooling air line. A heat exchanger is arranged in the second cooling air line for cooling the extracted air of higher pressure. The heat exchanger is connected with an air inlet side of the compressor such that heat is transferred in order to heat up the inlet air of the compressor.

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: A combustion chamber including a body with a fuel supply duct for supplying a fuel into the body and a carrier air supply duct for supplying air into the body. An adjusting system adjusts the carrier air mass flow supplied into the body according to the features of the fuel.

Abstract: The method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating the nitrogen (N2) percentage content as the complement to 100 of the measured percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (?) of the operative burners (9) of the second combustor (15) is kept below a maximum air ratio (?max) at part load In order to reduce the maximum air ratio (?), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes (14) before engaging the second combustor (15). For engaging the second combustor, the row of variable compressor inlet guide vanes (14) is quickly closed and fuel is introduced in a synchronized manner into the burner (9) of the second combustor (15). A further modification is the deactivating of individual burners (9) at part load.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (?) of the operative burners (9) of the second combustor (15) is kept below a maximum air ratio (?max) at part load In order to reduce the maximum air ratio (?), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes (14) before engaging the second combustor (15). For engaging the second combustor, the row of variable compressor inlet guide vanes (14) is quickly closed and fuel is introduced in a synchronized manner into the burner (9) of the second combustor (15). A further modification is the deactivating of individual burners (9) at part load.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (?) of the operative burners (9) of the second combustor (15) is kept below a maximum air ratio (?max) at part load In order to reduce the maximum air ratio (?), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes (14) before engaging the second combustor (15). For engaging the second combustor, the row of variable compressor inlet guide vanes (14) is quickly closed and fuel is introduced in a synchronized manner into the burner (9) of the second combustor (15). A further modification is the deactivating of individual burners (9) at part load.

Abstract: A combustor arrangement for a gas turbine engine (31) has a split line (42) and a plurality of burners (20,37) arranged in an annular ring (40). The burners (46) of the combustor on either side of the split line (42) have a separation distance of at least two times the average separation distance between burners (48) distant from the split line (42).

Abstract: A modification method for reducing emissions from an annular shaped combustor of a gas turbine plant, having uniformly spaced circumferentially mounted premix burners (20), includes the steps of: removing at least one burner (20), thereby disrupting the spatial uniformity of the remaining the burners (20); and modifying the combustor air distribution system so as to compensate for the increased burner pressure drop of the remaining burners, thus enabling the modified combustor to operate at a load equivalent to the unmodified combustor. Emission reduction is enabled by the increase in the gas velocity of the burner for a given load further enabled by the flame stabilizing effect of disrupting the spatial uniformity.

Abstract: A modification method for reducing emissions from an annular shaped combustor of a gas turbine plant, having uniformly spaced circumferentially mounted premix burners (20), includes the steps of: removing at least one burner (20), thereby disrupting the spatial uniformity of the remaining the burners (20); and modifying the combustor air distribution system so as to compensate for the increased burner pressure drop of the remaining burners, thus enabling the modified combustor to operate at a load equivalent to the unmodified combustor. Emission reduction is enabled by the increase in the gas velocity of the burner for a given load further enabled by the flame stabilizing effect of disrupting the spatial uniformity.

Abstract: A combustor arrangement for a gas turbine engine (31) has a split line (42) and a plurality of burners (20,37) arranged in an annular ring (40). The burners (46) of the combustor on either side of the split line (42) have a separation distance of at least two times the average separation distance between burners (48) distant from the split line (42).

Abstract: What is described is a burner system with a premix burner (1), in which is provided at least one vortex generator (2), through which passes an air-containing gaseous main flow (ZL) which flows axially through the premix burner (1) and into which gaseous and/or liquid fuel is injected, downstream of the vortex generator (2), as a secondary flow for generating a fuel/air mixture, and with a combustion chamber (5) which adjoins the premix burner (1) downstream of the latter and has a combustion chamber cross section (C2) which is larger than the flow cross section (C1), delimited by the premix burner (1), directly upstream of the combustion chamber (5).

Abstract: What is described is a burner system with a premix burner (1), in which is provided at least one vortex generator (2), through which passes an air-containing gaseous main flow (ZL) which flows axially through the premix burner (1) and into which gaseous and/or liquid fuel is injected, downstream of the vortex generator (2), as a secondary flow for generating a fuel/air mixture, and with a combustion chamber (5) which adjoins the premix burner (1) downstream of the latter and has a combustion chamber cross section (C2) which is larger than the flow cross section (C1), delimited by the premix burner (1), directly upstream of the combustion chamber (5).