SUPERCRITICAL CO2 CYCLE FOR GAS TURBINE ENGINES USING POWERED COOLING FLOW

Gas turbine engines 400; 500; 600 are described. The gas turbine engines 400; 500; 600 includes a compressor section, a combustor section, a turbine section, and a nozzle section. The compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that...

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Bibliographische Detailangaben
Hauptverfasser:	STAUBACH, Joseph B, BOUCHER, Amanda J. L
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	Gas turbine engines 400; 500; 600 are described. The gas turbine engines 400; 500; 600 includes a compressor section, a combustor section, a turbine section, and a nozzle section. The compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. A cooling duct 407; 507; 638 is provided that is separate from the core flow path. A waste heat recovery system 402; 502; 602 is arranged with a heat rejection heat exchanger 428; 528; 628 arranged within the cooling duct 407; 507; 638 and a blower 436; 536; 636 is arranged within the cooling duct 407; 507; 638 and configured to generate a pressure drop across the heat rejection heat exchanger 428; 528; 628.