Cooling air and injected liquid system for gas turbine blades

A gas turbine with a turbine comprising:

• a swivel-mounted rotationally symmetrical rotor;
• a compressor mounted along the rotor;
• a combustion chamber mounted along the rotor;
• a turbine section mounted along the rotor formed of a plurality of turbine stages in which each turbine stage comprises mutually interacting blades and vanes which are surrounded by a flow of hot working fluid;
• and
• a coolant provided by the compressor for cooling the blades and the vanes, The coolant flowing in a channel along the rotor from the compressor to the turbine section and into which a liquid is adapted to be introduced for cooling, wherein the channel extends outside the rotor, and the liquid is introduced into the channel in a region close to the compressor,
• wherein a flow channel downstream of the compressor outlet in the direction of flow of the compressor air contains a at least one passing through said flow channel,
• wherein a radially external end of the at least one is secured on the stator of the turbine and the radially internal end opposite the external end faces the rotor,
• wherein at least one rib is hollow and a pipe runs in the rib, the pipe communicating on a stator side with a source of liquid and on the rotor side with a nozzle used to introduce the liquid in the channel.

A turbine, comprising:

• a rotationally supported rotor shaft having an axis of rotation along a longitudinal axis of the rotor;
• a compressor arranged concentric with and surrounding the rotor;
• an annular flow channel arranged concentric with the rotor and downstream of an outlet of the compressor with respect to a flow direction of a working fluid of the turbine, the annular flow channel having a hollow diffuser rib passing through the flow channel, wherein
• a radially external end of the diffuser rib is secured on a stator of the turbine and a radially internal end opposite the external end faces the rotor, and a liquid coolant supply pipe runs within the hollow rib to introduce the liquid into the annular channel;
• a combustion chamber arranged concentric with the rotor and downstream of the compressor;
• and
• a turbine section arranged along the rotor and formed from a plurality of turbine stages in which each turbine stage comprises mutually interacting blades and vanes surrounded by a flow of the working fluid.