GAS TURBINE ENGINE WITH IMPROVED BENDING RESISTANCE

A gas turbine engine (10) for an aircraft comprises: an engine core (11) comprising a lower pressure compressor (14) and a higher pressure compressor (15); an inner core casing (70) provided radially inwardly of the compressor blades of the compressor system; and an outer core casing (76) surrounding the compressor system, the inner core casing (70) and the outer core casing (76) defining a core working gas flow path (A) therebetween. The outer core casing (76) comprises a first flange connection (60), the first flange connection (60) having a first flange radius (104). A gas path radius (102) is defined as the outer radius of the core gas flow path (A) at the axial position of the first flange connection (60), and a gas path ratio of: