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 the unit (30) and with at least one inlet (51, 61) and with at least one outlet (54, 55) of an oiltank (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 thefirst oil circuit (43). 用于飞行器的气体涡轮机引擎（10），其包括供应有来自第一油通路（43）和第二油通路（45）的油的单元（30）。第一油通路（43）和第二油通路（45）各自与单元（30）的至少一个入口（48、49）并且与至少一个出口（50、60）以及与油箱（53）的至少一个入口（51、61）并且与至少一个出口（54、55）流体地耦合。第一油通路（43）和第二油通路（45）配置成接收来自油箱（53）的油并将接收的油引导至单