Abstract: A gas turbine includes a compressor, a combustor downstream from the compressor and a heat transfer system, wherein the heat transfer system receives a compressed working fluid from the compressor. A fluid coupling between the heat transfer system and the combustor, wherein the fluid coupling receives the compressed working fluid from the heat transfer system. A conditioner in fluid communication with the compressor and a fluid coupling between the heat transfer system and the conditioner, wherein the fluid coupling receives a cooling media from the heat transfer system. A method for operating the gas turbine includes flowing a compressed working fluid from the compressor to the heat transfer system, transferring heat energy from the compressed working fluid to the heat transfer system, flowing the compressed working fluid from the heat transfer system to a combustor, and flowing a cooling media from the heat transfer system to a compressor inlet.

Abstract: A fuel nozzle is provided and includes a nozzle body defining first and second interior regions for providing a supply of first and second fluids, a collar defining a third interior region and radial slots permitting radial ingress of a third fluid to the third interior region and a nozzle tip interposed between the nozzle body and the collar. The nozzle tip defines an annular slot, first discrete passageways by which the first fluid is communicated from the first interior region to the annular slot, second discrete passageways by which the first fluid is communicated from the annular slot to the radial slots, and third discrete passageways by which the second fluid is communicated from the second interior region to the radial slots.