A gas turbine engine (10) includes a first spool (16) of a primary flow path (216) and a second spool (12) of a secondary flow path (220). The second spool (12) is nonconcentric with the first spool (16). The second spool (12) includes a boost compressor (96) and a load compressor (104) in fluid communication with an inlet plenum (128). An inlet duct assembly (62) and an outlet duct assembly (130) place the secondary flow path (220) in communication with the primary flow path (216). The gas turbine (100) includes a controller operable to vary open areas of variable inlet guide vanes to control a flow division between the boost compressor (96) and the load compressor (104).