WORK RECOVERY SYSTEM FOR A GAS TURBINE ENGINE UTILIZING A RECUPERATED SUPERCRITICAL CO2 CYCLE DRIVEN BY COOLED COOLING AIR WASTE HEAT

A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger...

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Bibliographische Detailangaben
Hauptverfasser:	Staubach, Joseph B, McAuliffe, Brendan T, Somanath, Nagendra
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL ENGINE PLANTS NOT OTHERWISE PROVIDED FOR ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING STEAM ACCUMULATORS STEAM ENGINE PLANTS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) coolant circuit and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is a recuperated Brayton cycle