An architecture configured for powering systems on an aircraft, the architecture comprising: a gas turbine engine including a main compressor, a combustor, and a turbine, said turbine powering said main compressor, and further configured for powering a propulsor; a generator; a battery; a motor; and said turbine also being operably connected to drive said generator, said generator being connected to store generated power at said battery, said battery being connected to provide power to said motor to power said propulsor such that said propulsor can be selectively driven by both said motor and said turbine; characterised by: a bleed air control system, and a tap for selectively tapping compressed air from said main compressor, and a control valve for delivering at least one of said tapped compressed air or a compressed alternative air to bleed systems on the aircraft; and an electric bleed compressor for selectively compressing the alternative air, said electric bleed compressor powered by said battery, and a control for controlling said control valve to selectively deliver at least one of said tapped compressed air and said compressed alternative air to said bleed systems, wherein, during high power condition of the propulsor, said battery is utilized to drive the motor, and said bleed air control system provides tapped compressed air to said bleed systems, but during lower power condition of the propulsor, said battery powers said electric bleed compressor to deliver said compressed alternative air to said bleed systems. a gas turbine engine including a main compressor, a combustor, and a turbine, said turbine powering said main compressor, and further configured for powering a propulsor; a generator; a battery; a motor; and said turbine also being operably connected to drive said generator, said generator being connected to store generated power at said battery, said battery being connected to provide power to said motor to power said propulsor such that said propulsor can be selectively driven by both said motor and said turbine; characterised by: a bleed air control system, and a tap for selectively tapping compressed air from said main compressor, and a control valve for delivering at least one of said tapped compressed air or a compressed alternative air to bleed systems on the aircraft; and an electric bleed compressor for selectively compressing the alternative air, said electric bleed compressor powered by said battery, and a control for controlling said control valve to selectively deliver at least one of said tapped compressed air and said compressed alternative air to said bleed systems, wherein, during high power condition of the propulsor, said battery is utilized to drive the motor, and said bleed air control system provides tapped compressed air to said bleed systems, but during lower power condition of the propulsor, said battery powers said electric bleed compressor to deliver said compressed alternative air to said bleed systems. a bleed air control system, and a tap for selectively tapping compressed air from said main compressor, and a control valve for delivering at least one of said tapped compressed air or a compressed alternative air to bleed systems on the aircraft; and an electric bleed compressor for selectively compressing the alternative air, said electric bleed compressor powered by said battery, and a control for controlling said control valve to selectively deliver at least one of said tapped compressed air and said compressed alternative air to said bleed systems, wherein, during high power condition of the propulsor, said battery is utilized to drive the motor, and said bleed air control system provides tapped compressed air to said bleed systems, but during lower power condition of the propulsor, said battery powers said electric bleed compressor to deliver said compressed alternative air to said bleed systems.