Gas turbine engine

A gas turbine engine for an aircraft comprising:

• a fan located adjacent an air intake of the engine, the fan comprising a plurality of fan blades;
• downstream of the fan, an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
• an engine core housing at least partly encasing the engine core;
• a fan case surrounding the fan and defining at least a part of a bypass duct radially outside the engine core;
• a plurality of outlet guide vanes extending between the engine core housing and an outlet guide vane support region of the fan case, adjacent an upstream end of the bypass duct;
• one or more supports extending from the fan case to the engine core housing,
• wherein:
• a first end of the one or more supports is fixed to the fan case at the outlet guide vane support region;
• and
• a second end of the one or more supports is fixed to the engine core housing adjacent an exhaust of the engine core.