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AssigneeROLLS-ROYCE plc
InventorsChathura K Kannangara, Jillian C Gaskell, Stewart T Thornton, Timothy Philp
Estimating the term…
A gas turbine engine includes an engine core and a fan located upstream of the engine core. The engine core includes: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection. The first flange connection 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 and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor. A fan diameter ratio of: first flange radius fan diameter is equal to or greater than 0.125.
A gas turbine engine for an aircraft comprising:
Dependencies are inferred from the claim text.