An apparatus comprising: a gas turbine engine having a first annular flow path disposed radially inward of a second annular flow path and at least two spool shafts (60a, 60b); and at least two rotatable shafts (68a, 68b) extending across the first annular flow path of the gas turbine engine and rotatingly coupled with at least one of the spool shafts (60a, 60b); wherein the at least two spool shafts (60a, 60b) include a first pressure spool shaft and a second pressure spool shaft, and wherein one of the at least two rotatable shafts (68a, 68b) is driven by the first pressure spool shaft, and another of the at least two rotatable shafts (68a, 68b) is driven by the second pressure spool shaft; and wherein the at least two rotatable shafts (68a, 68b) are circumferentially offset from each other; characterized by a first plurality of power devices in power communication with one of the at least two rotatable shafts (68a, 68b) and disposed between the first annular flow path and the second annular flow path within a fan frame of the gas turbine engine; and a second plurality of power devices apart from the first plurality of power devices, wherein the second plurality of power devices is in power communication with another of the at least two rotatable shafts (68a, 68b) and is disposed within the fan frame of the gas turbine engine; wherein at least one power device of the first plurality of power devices and at least one power device of the second plurality of power devices are configured to either provide power to or generate power from the at least two spool shafts for sharing the load between the at least two spool shafts (60a, 60b). a gas turbine engine having a first annular flow path disposed radially inward of a second annular flow path and at least two spool shafts (60a, 60b); and at least two rotatable shafts (68a, 68b) extending across the first annular flow path of the gas turbine engine and rotatingly coupled with at least one of the spool shafts (60a, 60b); wherein the at least two spool shafts (60a, 60b) include a first pressure spool shaft and a second pressure spool shaft, and wherein one of the at least two rotatable shafts (68a, 68b) is driven by the first pressure spool shaft, and another of the at least two rotatable shafts (68a, 68b) is driven by the second pressure spool shaft; and wherein the at least two rotatable shafts (68a, 68b) are circumferentially offset from each other; characterized by a first plurality of power devices in power communication with one of the at least two rotatable shafts (68a, 68b) and disposed between the first annular flow path and the second annular flow path within a fan frame of the gas turbine engine; and a second plurality of power devices apart from the first plurality of power devices, wherein the second plurality of power devices is in power communication with another of the at least two rotatable shafts (68a, 68b) and is disposed within the fan frame of the gas turbine engine; wherein at least one power device of the first plurality of power devices and at least one power device of the second plurality of power devices are configured to either provide power to or generate power from the at least two spool shafts for sharing the load between the at least two spool shafts (60a, 60b).