Method and apparatus for operating a gas turbine, with fuel injected into its compressor

摘要

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.