Filling lubricant tank for aircraft turbine engine

A dual flow turbine engine (10) comprising:-at least one lubricant tank (40) located in an annular space of a turbine engine body,-at least one hatch (46) provided on an outer cowl (32) of a nacelle for filling the tank, the canister is configured to be filled by a removable tubular conduit (50) ins...

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Bibliographische Detailangaben
1. Verfasser:	BERGO CLAIRE ALEXIA
Format:	Patent
Sprache:	chi ; eng
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 JET-PROPULSION 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 dual flow turbine engine (10) comprising:-at least one lubricant tank (40) located in an annular space of a turbine engine body,-at least one hatch (46) provided on an outer cowl (32) of a nacelle for filling the tank, the canister is configured to be filled by a removable tubular conduit (50) inserted into the canister from the hatch through the barrels, one of the barrels comprising a first interface (44) through which the conduit is configured, and the other of the barrels comprising a second interface (42) for connecting the conduit to the canister. 双流涡轮发动机(10)，包括：-至少一个润滑剂罐(40)，至少一个润滑剂罐位于涡轮发动机主体的环形空间中，-至少一个舱口(46)，至少一个舱口被设置在机舱的外部整流罩(32)上，以用于填充罐，该罐被构造为通过从舱口穿过筒体插入到罐中的可移除的管状管道(50)来填充，筒体中的一个包括第一接口(44)，管道被构造为穿过第一接口，筒体中的另一个包括用于将管道连接到罐的第二接口(42)。