Pulse detonation system for a gas turbine engine having multiple spools

A gas turbine engine (10) having a longitudinal centerline axis (12) therethrough, including: a fan section (20) at a forward end of the gas turbine engine (10) including at least a first fan blade row connected to a first drive shaft (32); a booster compressor (28) positioned downstream of the fan section (20), the booster compressor (28) including a first compressor blade row and a second compressor blade row connected to a second drive shaft (33) and interdigitated with the first compressor blade row; and, a pulse detonation system (46) for powering the first and second drive shafts (32, 33). The pulse detonation system (46) powers only the second drive shaft (33) during a first designated condition of the gas turbine engine (10) and both the first drive shaft (32) and the second drive shaft (33) during a second designated condition of the gas turbine engine (10). The first and second drive shafts (32, 33) are powered independently of each other by the pulse detonation system (46).