Patent ID: 10837370

Abstract:
A gas turbine engine including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft mounting structure that includes supporting bearings connected to the fan shaft; and an epicyclic gearbox that can receive input from the core shaft, and output drive to the fan shaft so as to drive the fan at a lower rotational speed than the core shaft. The gearbox includes a sun gear, planet gears, a ring gear, and a planet carrier for mounting the planet gears. A torsional stiffness of the planet carrier is greater than or equal to 1.6×108 Nm/rad. The fan shaft mounting structure has: a radial bending stiffness greater than or equal to 7.00×108 N/m, and/or a tilt stiffness greater than or equal to 1.50×107 Nm/rad.