Accessory gearbox

There is provided a method (300) of operating a gas turbine engine (10). The gas turbine engine (10) comprises an accessory gearbox (110) configured to power one or more engine accessories, and a combustor (16) in which fuel is combusted and a fuel-oil heat exchanger (114) arranged to transfer heat...

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Bibliographische Detailangaben
Hauptverfasser:	Craig W Bemment, Christopher P Madden, Benjamin J Keeler, Martin K Yates, Paul W Ferra, Peter Swann, Andrea Minelli
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	There is provided a method (300) of operating a gas turbine engine (10). The gas turbine engine (10) comprises an accessory gearbox (110) configured to power one or more engine accessories, and a combustor (16) in which fuel is combusted and a fuel-oil heat exchanger (114) arranged to transfer heat between oil and fuel that is provided to the combustor (16). An average temperature of lubricating oil is at least 180°C on exit from the accessory gearbox (110) at cruise conditions. The method (300) comprises transferring heat (301) from the oil to the fuel before the fuel enters the combustor (16) so as to raise the fuel temperature to an average of at least 135°C on entry to the combustor (16) at cruise conditions. Also provided is a gas turbine engine.