Abstract: A method for operating a gas turbine plant utilizing sequential combustion is provided. The gas turbine plant includes a compressor for compressing inducted combustion air, a first combustion chamber for combustion of a first fuel by utilizing the compressed combustion air, with a first turbine which is connected downstream of the first combustion chamber, and a second combustion chamber for combustion of a second fuel by utilizing the gases which emerge from the first turbine, with a second turbine which is connected downstream of the second combustion chamber. The method provides quick running up with simultaneously low emissions and homogeneous distribution of the turbine inlet temperature is achieved by the second combustion chamber being completely shut down for achieving a low partial load mode of the gas turbine plant.

Abstract: A method for operating a gas turbine plant utilizing sequential combustion is provided. The gas turbine plant includes a compressor for compressing inducted combustion air, a first combustion chamber for combustion of a first fuel by utilizing the compressed combustion air, with a first turbine which is connected downstream of the first combustion chamber, and a second combustion chamber for combustion of a second fuel by utilizing the gases which emerge from the first turbine, with a second turbine which is connected downstream of the second combustion chamber. The method provides quick running up with simultaneously low emissions and homogeneous distribution of the turbine inlet temperature is achieved by the second combustion chamber being completely shut down for achieving a low partial load mode of the gas turbine plant.

Abstract: In a method of operating a gas-turbine group having sequential combustion, action is taken first of all on the inlet temperatures (A, B) at the two turbines (6, 10) in order to provide a partial-load operation. The subsequent lowering of the load takes place by adjustment of the compressor guide blades (C), that is, by reducing the mass flow (E) to below 50% of the rated load (X). During this lowering, the inlet temperature (A) at the first turbine (6) is kept constant, while the other inlet temperature (B) at the second turbine (10) is continuously lowered; the outlet temperature (D) of the second turbine (10) is in contrast kept constant. After the lowering of the load is complete by adjusting the compressor guide blades, the inlet temperatures (A, B) are reduced directly or in a phase-displaced manner (Y).

Abstract: A method of establishing part-load operation is proposed for a turbine group. This gas turbine group consists essentially of a compressor unit (1), of an HP combustion chamber (4) downstream of the compressor unit (1), of an HP turbine (5) downstream of this HP combustion chamber (4), of an LP combustion chamber (8) operating by self-ignition and arranged downstream of the HP turbine (5), the hot gases (10) of which LP combustion chamber (8) being admitted to an LP turbine (11). The temperature at outlet from the HP turbine (5) remains essentially the same due to the reduction of the fuel quantity in the LP combustion chamber (8) to zero. Furthermore, the fuel quantity of the HP combustion chamber (4) remains approximately constant during the reduction of the fuel quantity in the LP combustion chamber (8) so that the temperature at inlet to the HP turbine (5) likewise remains constant.

Abstract: In a method of operating a gas turbine group (34) with or without integrated steam process (20) and with or without an air reservoir installation (20), a series connection with one and the same air mass flow (16, 17) is used for cooling one or more structures (15, 18, 19) which are in effective connection with the mass flow of the gas turbine group (34), the cooling air mass flow being extracted from a position which has a sufficiently low temperature.