Cooling system for a gas turbine and corresponding operation method
An operation method for a gas turbine is provided which includes compressing a working fluid by a compressor, feeding this compressed working fluid into at least one combustion chamber where it is overheated, expanding this overheated working fluid in at least one expansion turbine to produce energy, carrying out a first tapping of the compressed work fluid from the compressor to feed it into a first cavity of the turbine for cooling, carrying out a second tapping of the working fluid downstream from the first tapping to feed it into a second cavity of the turbine upstream from the first cavity, for cooling, and fluidly connecting the first tapping to the second tapping to selectively feed the first tapping by a part of the second tapping during partial load operation conditions to keep the temperature of the first cavity within the acceptable limits for the resistance of the materials.
1. A cooling system for a gas turbine comprising:
a first duct configured to feed a compressed working fluid from a first tapping of the compressed working fluid from a compressor to a first cavity for cooling of an expansion turbine;
a second duct configured to feed the compressed working fluid from a second tapping of the compressed working fluid of the compressor to a second cavity for cooling of an expansion turbine, wherein the second duct is at a higher pressure than the first duct, and wherein the second tapping is downstream from the first tapping;
a fluid dynamic system comprising an ejector directly coupled to the first duct, the ejector configured to prevent the working fluid from returning to the compressor;
wherein the fluid-dynamic system is configured to selectively combine the working fluid from the first tapping to the working fluid of the second tapping to selectively increase the flow of the working fluid of the first tapping during partial load operation conditions to keep the temperature at least in the first cavity within acceptable limits for the protection of the materials of the gas turbine therearound; and
a control system electronically connected to the fluid-dynamic system configured to selectively feed a part of the working fluid from the second tapping into the first duct during partial load operation conditions, based on the monitoring of operating parameters, to keep the temperature of the first cavity within the acceptable limits for the protection of the materials of the gas turbine engine therearound.
2. The cooling system of claim 1 , further configured to directly or indirectly monitor the temperature in at least the first cavity for cooling of the expansion turbine.
3. The cooling system of claim 1 , wherein the ejector is fluidly associated to the first duct and a connecting duct with a connection valve configured to fluidly connect the ejector with the connector duct.
4. A gas turbine comprising the cooling system of claim 1 .