Partial exhaust condensation intercooling

An aircraft propulsion system comprising:

• a compressor section where an inlet airflow is compressed to generate a compressed airflow;
• a combustor section where the compressed airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path;
• a turbine section through which the exhaust gas flow expands to generate a mechanical power output, wherein the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow;
• and
• a condenser where water is extracted from the second exhaust gas flow to generate an extracted water flow;
• a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path;
• and
• a control device configured to vary a ratio of the first exhaust gas flow to the second exhaust gas flow and a controller programmed to operate the control device based upon information indicative of at least one operating condition.

An aircraft propulsion system comprising:

• a compressor section where an inlet airflow is compressed to generate a compressed airflow;
• a combustor section where the compressed airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path;
• a turbine section through which the exhaust gas flow expands to generate a mechanical power output, wherein the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow;
• and
• a condenser where water is extracted from the second exhaust gas flow to generate an extracted water flow;
• a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path;
• and
• a mixer where the first exhaust gas flow and the second exhaust gas flow are recombined and exhausted through a nozzle.

A turbine engine assembly comprising:

• a core engine defining a core flow path and configured to generate an exhaust gas flow;
• a condenser configured to receive a partial portion of the exhaust gas flow and to extract water from the partial portion of the exhaust gas flow to generate an extracted water flow, wherein the partial portion of the exhaust gas flow is tapped from a location in the turbine section that is upstream of an aft exit;
• and
• a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path.

A method of operating a turbine engine including a cryogenic fuel system comprising:

• splitting a total exhaust gas flow into a first exhaust gas flow and a second exhaust gas flow such that the second exhaust gas flow is of a flow volume less than that of the first exhaust gas flow;
• cooling the second exhaust gas flow to condense water into a liquid form, wherein a portion of a cryogenic fuel flow from the cryogenic fuel system accepts thermal energy from the second exhaust gas flow;
• extracting liquid water from the partial portion of the second exhaust gas flow to generate an extracted water flow;
• and
• cooling a portion of a core flow along a core flow path by injecting a portion of the extracted water flow into the core flow path.