A gas turbine engine (10) for an aircraft comprising: an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor; a fan (23) located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox (30) that receives an input from the core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, the gearbox (30) being an epicyclic gearbox (30) comprising a sun gear (28), a plurality of planet gears (32), a ring gear (38), and a planet carrier (34) arranged to have the plurality of planet gears (32) mounted thereon; and a gearbox support (40) arranged to at least partially support the gearbox within the engine. A flight cycle ratio of: the torsional shear stress of the gearbox support 40 at maximum takeoff conditions the torsional shear stress of the gearbox support 40 at cruise conditions is in the range of from is less than or equal to 3.20. A method (2000) of operating the gas turbine engine is also disclosed.
本发明题为飞行器引擎。本公开提供了一种用于飞行器的气体涡轮引擎(10),该气体涡轮引擎包括:引擎核心(11),该引擎核心包括涡轮(19)、压缩机(14)以及将该涡轮连接到该压缩机的芯轴(26);风扇(23),该风扇位于该引擎核心的上游,该风扇包括多个风扇叶片;齿轮箱(30),该齿轮箱接收来自该芯轴(26)的输入,并且将驱动输出至该风扇,以便以比该芯轴低的旋转速度驱动该风扇,该齿轮箱(30)是周转齿轮箱(30),该周转齿轮箱包括太阳齿轮(28)、多个行星齿轮(32)、环形齿轮(38)以及被布置用于将该行星齿轮(32)安装在其上的行星架(34);以及齿轮箱支撑件(40),该齿轮箱支撑件被布置用于至少部分地支撑该引擎内的齿轮箱。飞行周期比率:小于或等于3.20。本发明还公开了一种操作气体涡轮引擎的方法(2000)。
AIRCRAFT ENGINE
飞行器引擎
2021-06-08
Patent
Electronic Resource
Chinese