GAS TURBINE ENGINE WITH CABIN BLOWER SYSTEM

A gas turbine engine 200, 200', 200" for mounting to an airframe of an aircraft comprises an engine core 210; a fan 214 located upstream of the engine core 210; a bifurcation 204 spanning a bypass duct 202 defined between the engine core 210 and a nacelle 221 surrounding the gas turbine engine 200, 200', 200", the bifurcation 204 comprising aerodynamically shaped fairings 206 defining an interior space 208 therebetween; and a cabin blower system 100 arranged in the interior space 208 of the bifurcation 204.