System and method for thermal control in a gas turbine engine

A system includes a gas turbine engine (12) that includes a compressor section (16) configured to generate compressed air (24) and a combustor (18) coupled to the compressor section (16). The combustor (18) is configured to combust a first mixture comprising the compressed air (24) and a first fuel...

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Bibliographische Detailangaben
Hauptverfasser:	THACKER, PRADEEP STANLEY, AVAGLIANO, AARON JOHN
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 LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A system includes a gas turbine engine (12) that includes a compressor section (16) configured to generate compressed air (24) and a combustor (18) coupled to the compressor section (16). The combustor (18) is configured to combust a first mixture comprising the compressed air (24) and a first fuel (26) to generate a first combustion gas (28). The gas turbine engine (12) also includes a turbine section (20) coupled to the combustor (18). The turbine section (20) is configured to expand the first combustion gas (28) to generate an exhaust gas (28). The gas turbine engine (12) also includes a boiler (34) coupled to the turbine section (20). The boiler (34) is configured to combust a second mixture comprising a portion (36) of the first combustion gas (28) and a second fuel to generate a second combustion gas (38) that is routed to the turbine section (20). In addition, the boiler (34) generates a first steam (40) from heat exchange with the second combustion gas (38).