GAS TURBINE ENGINE

A gas turbine engine (10) for an aircraft comprises a unit (30) supplied with oil from a first oil circuit (43) and a second oil circuit (45). The first oil circuit (43) and the second oil circuit (45) each are fluidly coupled with at least one inlet (48, 49) and with at least one outlet (50, 60) of...

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Bibliographische Detailangaben
Hauptverfasser:	Uhkötter, Stephan, Edwards, David, Hammond, Lynn, Williams, David, Davies, Neil, Menczykalski, Stefan, Mason, John R
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 ENGINE PLANTS IN GENERAL 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 STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (10) for an aircraft comprises a unit (30) supplied with oil from a first oil circuit (43) and a second oil circuit (45). The first oil circuit (43) and the second oil circuit (45) each are fluidly coupled with at least one inlet (48, 49) and with at least one outlet (50, 60) of the unit (30) and with at least one inlet (51, 61) and with at least one outlet (54, 55) of an oil tank (53). The first oil circuit (43) and the second oil circuit (45) are configured to receive oil from the oil tank (53) and to direct the received oil to the unit (30). The oil tank (53) is incorporating offset outlets (25, 29) to each of the oil circuits (43, 45). The offset outlet (29) of the second oil (45) circuit is positioned higher in the oil tank (53) than the offset outlet (25) of the first oil circuit (43). The second oil circuit (45) comprises a sensor (52) for sensing a feeding pressure in the second oil circuit (45). A warning signal is generated when a feeding pressure in the second oil circuit (45) is less than or equal to a predefined value.