Abstract: The invention relates to a gas turbine (3) with reheat in the turbine section (11), whereby a fuel injection device (37) is provided for the injection of fuel (33) in to a combustion air flow (61) in the direction of flow before a cooling air flow (65) branching. By means of the early mixing of fuel (63) in the combustion air flow (61) and concomitant additional use of the cooling air flow (65) as combustion air, the specific output and the efficiency of the gas turbine (3) are improved.

Abstract: A gas turbine with reheat in the turbine section includes a fuel injection device for the injection of fuel in to a combustion air flow in the direction of flow before a cooling air flow branching. By way of the early mixing of fuel in the combustion air flow and concomitant additional use of the cooling air flow as combustion air, the specific output and the efficiency of the gas turbine are improved.

Abstract: Combustion air or a combustion air/fuel mixture is supplied in a flow to a combustion process of a burner. A swirl, which is non-uniform in the peripheral direction, is imposed on the flow. A flow duct, in which is arranged a swirl device for imposing the swirl, is used for the supply of the combustion air or the combustion air/fuel mixture. As such, combustion oxcillations are reduced.

Abstract: A gas turbine and a method for combustion of a fuel in a gas turbine, conduct a flow of compressed air through the gas turbine from a compressor section to a turbine section. The fuel is fed to the flow in the compressor section and is burnt in the flow between the compressor section and the turbine section. The flow is subjected to a spin with a speed component at right angles to a movement direction of the flow when the flow emerges from the compressor section. The combustion of the fuel increases the speed component in the movement direction of the flow, causing the speed of the flow entering the turbine section to correspond to a value predetermined by the geometry of the turbine section.

Abstract: A method of expanding a hot flue-gas flow in a turbine through which a hot flue-gas passes. A structural component of the turbine is cooled by a cooling-gas flow which flows through the structural component and is fed to the hot flue-gas flow. Fuel is added in a metered fashion to the flue-gas flow in the turbine in such a way that a temperature drop in the flue-gas flow, which temperature drop results from the feeding of the cooling-gas flow without a metered addition of the fuel, is largely compensated for by the combustion of the fuel added in a metered fashion to the hot flue-gas flow. A corresponding turbine is also taught.