Abstract: A method for controlling a gas turbine assembly includes: a compressor in which compression of the outside air occurs for producing a flow of compressed air; a sequential combustor including a first combustor, in which combustion of a mixture of fuel and compressed air arriving from the compressor occurs for producing a flow of hot gasses, and a second combustor which is located downstream of the first combustor and in which combustion of a mixture of fuel and hot gasses arriving from the first combustor occurs; an intermediate turbine in which a partial expansion of the hot gasses arriving from the first combustor occurs; and a second combustor in which combustion of a mixture of fuel and hot gasses arriving from the intermediate turbine occurs; the method further includes, on a start-up transient operating phase of the gas turbine assembly, the step of controlling the fuel mass flow-rate supplied to the first and/or the second combustor on the basis of the flame temperature inside the first combustor.

Abstract: The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the opening of the row of variable compressor inlet guide vanes is controlled depending on the temperatures of the operative burners of the second combustor and simultaneously the number of operative burners is kept at a minimum. This leads to low CO emissions at partial load of the gas turbine.

Abstract: In a method for switching over a gas turbine plant from gaseous fuel (16, 20) to liquid fuel (18, 22) and vice-versa, in which the gas turbine plant includes a first combustor and a second combustor fed with the flue gases of the first combustor, the first and second combustors are sequentially switched over while the other combustor maintains its operating conditions.

Abstract: A method of controlling the fuel distribution among different stages of a gas turbine combustion chamber is disclosed. The combustion chamber has at least two stages for fuel supply, and the fuel distribution between the stages is determined according to the load or one or more parameters indicative of the load. In reply to a fast load change being faster than a load change during a regular transient operation, the fuel distribution is determined according to an adjusted load or one or more parameters indicative of an adjusted load.

Abstract: A method is provided for switching over a gas turbine burner operation from liquid fuel to gas fuel and vice-versa, with the burner comprising nozzles for feeding a premixed gas fuel, nozzles for injecting a pilot gas fuel and nozzles for injecting a liquid fuel. According to the method, while the liquid fuel and the premix gas fuel are regulated to switch over from liquid fuel to gas fuel operation or vice-versa, the pilot gas fuel is controlled at a substantially constant flow rate.

Abstract: The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the opening of the row of variable compressor inlet guide vanes is controlled depending on the temperatures of the operative burners of the second combustor and simultaneously the number of operative burners is kept at a minimum. This leads to low CO emissions at partial load of the gas turbine.

Abstract: A gas turbine plant has a compressor (2), a first combustion chamber (6) followed by a high pressure turbine (4), a second combustion chamber (10) and a low pressure turbine (5). In the first combustion chamber (6) a first gaseous fuel (8) is injected and combusted, generating first hot gases (9) that are at least partly expanded in the high pressure turbine (4), and in the second combustion chamber (10) a second fuel (11) is injected in the at least partly expanded hot gases generated in the first combustion chamber (6) and combusted, generating second hot gases (12) that are expanded in the low pressure turbine (5). In the first combustion chamber (6) water is also injected to increase the gas turbine plant power output. In the first combustion chamber (6) a water flow rate is injected compatible with a predetermined flame stability limit.

Abstract: A reheat combustor for a gas turbine engine includes a fuel/gas mixer for mixing fuel, air and combustion gases produced by a primary combustor and expanded through a high pressure turbine. Fuel injectors inject fuel into the mixer together with spent cooling air previously used for convectively cooling the reheat combustor. The fuel mixture is burnt in an annular reheat combustion chamber prior to expansion through low pressure turbine inlet guide vanes. The fuel/gas mixer and optionally the combustion chamber define cooling paths through which cooling air flows to convectively cool their walls. The fuel injectors are also convectively cooled by the cooling air after it has passed through the fuel/gas mixer cooling paths. The low pressure turbine inlet guide vanes may also define convective cooling paths in series with the combustion chamber cooling paths.

Abstract: A reheat combustor for a gas turbine engine includes a fuel/gas mixer for mixing fuel, air and combustion gases produced by a primary combustor and expanded through a high pressure turbine. Fuel injectors inject fuel into the mixer together with spent cooling air previously used for convectively cooling the reheat combustor. The fuel mixture is burnt in an annular reheat combustion chamber prior to expansion through low pressure turbine inlet guide vanes. The fuel/gas mixer and optionally the combustion chamber define cooling paths through which cooling air flows to convectively cool their walls. The fuel injectors are also convectively cooled by the cooling air after it has passed through the fuel/gas mixer cooling paths. The low pressure turbine inlet guide vanes may also define convective cooling paths in series with the combustion chamber cooling paths.

Abstract: A method is provided for switching over a gas turbine burner operation from liquid fuel to gas fuel and vice-versa, with the burner comprising nozzles for feeding a premixed gas fuel, nozzles for injecting a pilot gas fuel and nozzles for injecting a liquid fuel. According to the method, while the liquid fuel and the premix gas fuel are regulated to switch over from liquid fuel to gas fuel operation or vice-versa, the pilot gas fuel is controlled at a substantially constant flow rate.

Abstract: In a method for switching over a gas turbine plant from gaseous fuel (16, 20) to liquid fuel (18, 22) and vice-versa, in which the gas turbine plant includes a first combustor and a second combustor fed with the flue gases of the first combustor, the first and second combustors are sequentially switched over while the other combustor maintains its operating conditions.

Abstract: A gas turbine plant has a compressor (2), a first combustion chamber (6) followed by a high pressure turbine (4), a second combustion chamber (10) and a low pressure turbine (5). In the first combustion chamber (6) a first gaseous fuel (8) is injected and combusted, generating first hot gases (9) that are at least partly expanded in the high pressure turbine (4), and in the second combustion chamber (10) a second fuel (11) is injected in the at least partly expanded hot gases generated in the first combustion chamber (6) and combusted, generating second hot gases (12) that are expanded in the low pressure turbine (5). In the first combustion chamber (6) water is also injected to increase the gas turbine plant power output. In the first combustion chamber (6) a water flow rate is injected compatible with a predetermined flame stability limit.

Abstract: A device and a method for flame stabilization in a burner (10), includes a burner housing at least partially enclosing a burner volume, into which may be introduced via at least one fuel line, fuel, and via at least one air feed means, air, forming an air/fuel mixture spreading in a preferred flow direction, which may be ignited in a combustion chamber (11) connecting downstream of the burner housing to form a stationary flame (13). Upstream of the flame (13), a catalyst arrangement (1) is provided through which an air/pilot fuel mixture (4), separate from the air/fuel mixture, is flowable.

Abstract: A device and a method for flame stabilization in a burner (10), includes a burner housing at least partially enclosing a burner volume, into which may be introduced via at least one fuel line, fuel, and via at least one air feed means, air, forming an air/fuel mixture spreading in a preferred flow direction, which may be ignited in a combustion chamber (11) connecting downstream of the burner housing to form a stationary flame (13). Upstream of the flame (13), a catalyst arrangement (1) is provided through which an air/pilot fuel mixture (4), separate from the air/fuel mixture, is flowable.