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 a fan shaft 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 fan shaft mounting structure (503) arranged to mount the fan shaft within the engine, the fan shaft mounting structure (503) comprising at least two supporting bearings (506a, 506b) connected to the fan shaft (36). The torsional stiffness of the planet carrier (34) is greater than or equal to 1.6*10<8> Nm/rad. The radial bending stiffness of the fan shaft mounting structure (503) is greater than or equal to 7.00*10<8> N/m. The tilt stiffness of the fan shaft mounting structure (503) is greater than or equal to 1.50*10<7> Nm/rad.
本发明题为用于气体涡轮引擎的可靠齿轮箱。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),所述齿轮箱接收来自所述芯轴(26)的输入并将驱动输出至风扇轴,以便以比所述芯轴低的旋转速度驱动所述风扇,所述齿轮箱(30)是周转齿轮箱(30),所述周转齿轮箱包括太阳齿轮(28)、多个行星齿轮(32)、环形齿轮(38)以及被布置用于将所述多个行星齿轮(32)安装在其上的行星架(34);风扇轴安装结构(503),该风扇轴安装结构被布置成将该风扇轴安装在引擎内,该风扇轴安装结构(503)包括连接到风扇轴(36)的至少两个支撑轴承(506a,506b)。行星架(34)的抗扭刚度大于或等于1.6×108Nm/rad。风扇轴安装结构(503)的径向抗弯刚度大于或等于7.00×108N/m。风扇轴安装结构(503)的抗倾刚度大于或等于1.50×107Nm/rad。
RELIABLE GEARBOX FOR GAS TURBINE ENGINE
用于气体涡轮引擎的可靠齿轮箱
2021-06-08
Patent
Electronic Resource
Chinese