MULTIPLE TURBOEXPANDER SYSTEM HAVING SELECTIVE COUPLER

An aircraft propulsion system includes aircraft systems (304) having at least one hydrogen tank (332) and an aircraft-systems heat exchanger (358) and engine systems having at least a main engine core, a high pressure pump (316), a hydrogen-air heat exchanger (324), and a turbo expander assembly. The main engine core includes a compressor section, a combustor section having a burner (310), and a turbine section. Fuel is supplied from the at least one fuel tank (332) through a fuel flow path (344), passing through the aircraft-systems heat exchanger (358), the high pressure pump (316), the hydrogen-air heat exchanger (324), and selectively through the turbo expander assembly, prior to being injected into the burner (310) for combustion. The turbo expander assembly is operably coupled to at least two load sources through a selective coupler and configured to selectively drive operation of the at least two load sources.