INTER-COOLED PREHEAT OF STEAM INJECTED TURBINE ENGINE

A propulsion system for an aircraft includes a core engine that includes a core flow path (C) where a core flow (50) is compressed in a compressor section (24), communicated to a combustor section (30), mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section (32). A fuel system (56) is configured to supply a hydrogen based fuel to the combustor (30) through a fuel flow path (62). A condenser (72) is arranged along the core flow path (C) and configured to extract water from the gas flow. An intercooling system (90) receives a portion of water from the condenser (72) for cooling a portion of the core flow (50) at a first location within the compressor section (24). Heated water from the intercooling system (90) is exhausted to a second location within the core flow path (C) downstream of the first location.