Patent ID: 11920526
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 10:
11. A propulsion system for an aircraft comprising:
a core engine including a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section, wherein the compressor section includes a first compressor upstream of a second compressor;
a hydrogen fuel system configured to supply hydrogen fuel to the combustor section through a fuel flow path;
a condenser arranged along the core flow path and configured to extract a water flow from the gas flow;
an evaporator arranged along the core flow path and configured to receive a portion of the water extracted by the condenser to generate a steam flow, wherein the steam flow is injected into the core flow path upstream of the turbine section; and
an intercooling system comprising a preheater disposed within the compressor section, the preheater configured for transferring thermal energy from the core airflow into a portion of the water flow and communicating the resulting heated water flow to the evaporator and then into the core engine.