Intake and exhaust arrangement in a gas turbine engine

A gas turbine engine 10 comprises at least one engine rotor including a compressor 22 driven by a turbine 44, a combustion chamber 38, a compressor inlet 12, 30 and a turbine exhaust 20, 48, the inlet 12, 30 and/or exhaust 20, 48 being located between the compressor 22 and the turbine 44, and at least one output shaft 24', 24'' extending from an axial end of the engine 10. The shaft(s) 24', 24'' may drive an engine gearbox, or one or more engine accessory. The engine 10 may be a single spool engine, or may be a multi-spool engine (figure 2) comprising a plurality of single spools cascaded together.