Gas turbine engine

A gas turbine engine 10 comprises a combustor 16 and a fuel management system 500. The fuel management system 500 comprises a fuel supply line 510, a recirculation line 511 and a heat exchanger 540. The fuel supply line 510 is configured to supply fuel to the combustor 16. The recirculation line 511...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Richard G Mochrie, Jade Whittle, Graeme E F Sutcliffe
Format:	Patent
Sprache:	eng
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 gas turbine engine 10 comprises a combustor 16 and a fuel management system 500. The fuel management system 500 comprises a fuel supply line 510, a recirculation line 511 and a heat exchanger 540. The fuel supply line 510 is configured to supply fuel to the combustor 16. The recirculation line 511 is configured to recirculate excess fuel from the fuel supply line 510 to an engine-located fuel tank 560 via a fuel cooling device 570. The fuel cooling device 570 is configured to reject heat from the excess fuel in the recirculation line 511. The heat exchanger 540 is configured to reject heat from a thermal load 44 of the gas turbine engine 10 to fuel in the fuel management system 500. The heat exchanger 540 is disposed on the fuel supply line 510 or on the recirculation line 511. The fuel supply line 510 is configured to receive fuel from an external source 41 and from the engine-located fuel tank 560. Also provided is an aircraft 600 comprising the gas turbine engine 10 and an airframe 40 comprising an airframe-located fuel tank 41 which provides the external source 41 for the fuel supply 510.