ADJUSTABLE PRIMARY AND SUPPLEMENTAL POWER UNITS

A propulsion system (18) for an aircraft includes a core flow path (C) in communication with a compressor section (24), combustor section (26) and a turbine section (28). A first bottoming cycle system (62) includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the combustion section (24). The first bottoming cycle system (62) is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system (64) is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.