Oil system

A gas turbine engine (10, fig. 1) comprises an engine core (11, fig. 1) comprising a turbine (19, fig. 1), a compressor (14, fig. 1), a combustor (16, fig. 1), and a core shaft (26, fig. 1) connecting the turbine to the compressor; a fan (23, fig. 1) located upstream of the engine core; a fan shaft...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Craig W Bemment, Benjamin J Keeler, Kevin R McNally, 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:	A gas turbine engine (10, fig. 1) comprises an engine core (11, fig. 1) comprising a turbine (19, fig. 1), a compressor (14, fig. 1), a combustor (16, fig. 1), and a core shaft (26, fig. 1) connecting the turbine to the compressor; a fan (23, fig. 1) located upstream of the engine core; a fan shaft (42, fig. 1); a main gearbox (30, fig. 1) that receives an input from the core shaft and outputs drive to the fan via the fan shaft; an oil loop 2000 to lubricate the main gearbox; and a heat exchanger 1004 transferring heat between the oil and fuel. A method is also disclosed wherein at cruise conditions, the oil has an average temperature of at least 180°C on entry to the heat exchange system, and 200 to 600 kJ/m3 of heat is transferred from the oil to the fuel, using the heat exchanger. There may be a bypass 1005 around the heat exchanger to control oil temperature to the gearbox.