GAS TURBINE ENGINE WITH IMPROVED BENDING RESISTANCE

A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising: a first compressor (14), a second compressor (15) and an outer core casing (70) surrounding the compressors. The gas turbine engine further comprises a fan (23), the fan comprising a plurality of fan blades. The outer core casing comprises: a first flange connection (60) having a first flange radius (104), wherein the first flange connection (60) is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor (14) and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor (15) and a ratio first flange radius/mass of each blade is equal to or less than 19.0 mm/lb.