HYDROGEN STEAM INJECTED TURBINE ENGINE WITH COOLED COOLING AIR

A propulsion system for an aircraft includes a core engine (20) generating an exhaust gas flow (55) that is expanded through a turbine section (32), a hydrogen fuel system (52) suppling hydrogen fuel to the combustor (30) through a fuel flow path (45), a condenser (80) extracting water from the exhaust gas flow (55), an evaporator (112) receiving a portion of the water extracted by the condenser (80) and generating a steam flow (114). The steam flow (114) is injected into a core flow path (25) upstream of the turbine section (32) and a cooled cooling air system (100) uses water extracted from the exhaust gas flow (55) for cooling a cooling airflow (90, 120) communicated to the turbine section (32).