Bypass heat exchanger configuration to reroute core flow

1. A turbine engine assembly comprising:

a compressor section where an inlet airflow is compressed;

a combustor section where the compressed inlet airflow is mixed with fuel and ignited to generate an exhaust gas flow;

a turbine section through which the exhaust gas flow expands to generate a mechanical power output;

a condenser where water is extracted from the exhaust gas flow;

an evaporator in thermal communication with the exhaust gas flow and configured to use thermal energy from the exhaust gas flow to generate a steam flow from at least a portion of water extracted by the condenser for injection into a core flow path;

a bypass passage configured to selectively route at least a portion of the exhaust gas flow around at least one of the condenser and the evaporator in response to a predefined temperature indicative of a temperature at the at least one of the condenser and the evaporator; and

a flow control device operated by a controller, wherein the controller is configured to control an amount of available water and to control the flow control device to selectively direct the exhaust gas flow into the bypass passage based, at least in part, on information indicative of an amount of available water.

2. The turbine engine assembly as recited in claim 1 , including a sensor assembly communicating information indicative of a temperature at least one of the condenser and the evaporator to the controller.

3. The turbine engine assembly as recited in claim 2 , wherein the controller is programmed to operate the flow control device to route the exhaust gas flow into the bypass passage responsive to a sensed temperature of the at least one the condenser and the evaporator exceeding a predefined threshold temperature.

4. The turbine engine assembly as recited in claim 3 , wherein the controller is programmed to operate the flow control device to close the bypass passage such that the exhaust gas flow is directed through the at least one of the condenser and the evaporator in response to the sensed temperature returning below the predefined threshold temperature.

5. The turbine engine as recited in claim 1 , wherein only a portion of the exhaust gas flow is routed into the bypass passage.

6. The turbine engine as recited in claim 1 , wherein the bypass passage includes an outlet to exhaust bypassed exhaust gas flow to the ambient environment.

7. An aircraft propulsion system comprising:

a core engine section generating an exhaust gas flow;

a propulsor driven by the core engine;

a condenser where water is extracted from the exhaust gas flow;

an evaporator system where thermal energy from the exhaust gas flow is utilized to generate a steam flow from at least a portion of water extracted by the condenser for injection into the core engine; and

a bypass passage configured to selectively route at least a portion of the exhaust gas flow around at least one of the evaporator and the condenser in response to a predefined engine operating condition;

a flow control device operable for selectively directing the exhaust gas flow into the bypass passage; and

a controller programmed to operate the flow control device based on information indicative of an amount of water available for communication to the evaporator.

8. The aircraft propulsion system as recited in claim 7 , including a sensor assembly communicating information indicative of a temperature of at least one of the condenser or the evaporator system to the controller.

9. The aircraft propulsion system as recited in claim 8 , wherein the predefined engine operating condition is a temperature and the controller is programmed to operate the flow control device to route exhaust gas flow into the bypass passage responsive to a sensed temperature of at least one of the condenser or the evaporator system exceeding a predefined threshold temperature.

10. The aircraft propulsion system as recited in claim 9 , wherein the controller is programmed to operate the flow control device to close the bypass passage such that the exhaust gas flow is directed through the evaporator system and the condenser in response to the sensed temperature being below the predefined threshold temperature.

11. A method of operating an aircraft propulsion system, the method comprising:

generating an exhaust gas flow;

measuring an engine operating parameter indicative of a temperature of at least one of a condenser where water is extracted from the exhaust gas flow and an evaporator where thermal energy from the exhaust gas flow is utilized to generate a steam flow from at least a portion of water extracted by the condenser;

selectively operating a flow control device to selectively direct at least a portion of the exhaust gas flow around one or both of the condenser and the evaporator into a bypass passage in response to the measured engine operating parameter being indicative of a temperature exceeding a predefined threshold;

selectively operating the flow control device to direct the exhaust gas flow through the evaporator system and the condenser in response to the measured engine operating parameter being indicative of the temperature being below the predefined threshold temperature and directing exhaust gas flow through the evaporator and the condenser in response to a predefined amount of water being communicated to the evaporator.

12. The method as recited in claim 11 , wherein selectively routing at least a portion of the exhaust gas flow around one or both of the condenser and the evaporator comprises routing exhaust gas flow around the condenser.

13. The method as recited in claim 11 , wherein selectively routing at least a portion of the exhaust gas flow around one or both of the condenser and the evaporator comprises routing the exhaust gas flow around both the condenser and the evaporator.