SUPERCRITICAL CO2 CYCLE FOR GAS TURBINE ENGINES HAVING SUPPLEMENTAL COOLING

Gas turbine engines (500, 600, 700, 800, 900) are described. The gas turbine engines (500, 600, 700, 800, 900) include a compressor section, a combustor section, a turbine section, and a nozzle (520, 620, 720, 820, 920), wherein the compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle (520, 620, 720, 820, 920). A waste heat recovery system (502, 602, 702, 802, 902) is operably connected to the gas turbine engine (500, 600, 700, 800, 900), the waste heat recovery system (502, 602, 702, 802, 902) having a working fluid. An auxiliary cooling system (540, 640, 740, 840, 940) is configured to provide cooling to a working fluid of the waste heat recovery system (502, 602, 702, 802, 902).