Partial exhaust condensation regenerator
A turbine engine assembly generates an exhaust gas flow that is divided into a first exhaust gas flow and a second exhaust gas flow. A desiccation system transfers water vapor from the first exhaust gas flow into the second exhaust gas flow. A condenser extracts water from the second exhaust gas flow and an evaporator system uses thermal energy from the exhaust gas flow to generate a steam flow from at least a portion of water that is extracted by the condenser for injection into the core flow path.
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 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 divided into a first exhaust gas flow and a second exhaust gas flow, and the first exhaust gas flow is exhausted through a first nozzle and the second exhaust gas flow is exhausted through a second nozzle;
a desiccation system where water vapor from the first exhaust gas flow is concentrated and released into the second exhaust gas flow;
a condenser where water from the second exhaust gas flow is extracted; and
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 flow path.
2 . The turbine engine assembly as recited in claim 1 , wherein the desiccation system includes a first part and a second part that are interchanged between exposure to the first exhaust gas flow and the second exhaust gas flow.
3 . The turbine engine assembly as recited in claim 2 , wherein each of the first part and the second part absorbs water vapor when exposed to the first exhaust gas flow and releases moisture when exposed to the second exhaust gas flow.
4 . The turbine engine assembly as recited in claim 3 , wherein when the first part is exposed to the first exhaust gas flow, the second part is exposed to the second exhaust gas flow.
5 . The turbine engine assembly as recited in claim 4 , wherein the first part and the second part are part of a common rotating element for interchanging the first part and the second part between the first exhaust gas flow and the second exhaust gas flow.
6 . The turbine engine assembly as recited in claim 1 , including a precooler disposed between the evaporator system and the desiccation system.
7 . The turbine engine as recited in claim 1 , wherein the second exhaust gas flow is tapped from a location upstream of an aft exit of the turbine section.
8 . The turbine engine assembly as recited in claim 1 , wherein the evaporator system is in thermal communication with the first exhaust gas flow and the second exhaust gas flow is routed around the evaporator system.
9 . The turbine engine assembly as recited in claim 1 , wherein the evaporator system is in thermal communication with both the first exhaust gas flow and the second exhaust gas flow.
10 . The turbine engine assembly as recited in claim 1 , including secondary evaporator that is exposed to the second exhaust gas flow between the desiccation system and the condenser.
11 . An aircraft propulsion system comprising:
a propulsor section;
a core engine that defines a core flow path where an inlet airflow is compressed, mixed with fuel, and ignited to generate an exhaust gas flow that generates shaft power to drive the propulsor section, wherein the exhaust gas flow is divided into a first exhaust gas flow and a second exhaust gas flow, and the first exhaust gas flow is exhausted through a first nozzle and the second exhaust gas flow is exhausted through a second nozzle;
a desiccation system where a desiccant material absorbs water vapor from the first exhaust gas flow and releases the absorbed water vapor into the second exhaust gas flow;
a condenser configured for extracting water from the second exhaust gas flow;
an evaporator system configured to use thermal energy from the exhaust gas flow to vaporize water into a steam flow from at least a portion of water extracted by the condenser for injection into the core flow path.
12 . The aircraft propulsion system as recited in claim 11 , wherein the desiccation system comprises a means of interchanging different parts of the desiccant material between the first exhaust gas flow and the second exhaust gas flow.
13 . The aircraft propulsion system as recited in claim 12 , including a controller programed to interchange parts of the desiccation system to concentrate moisture within the second exhaust gas flow.
14 . The aircraft propulsion system as recited in claim 11 , wherein the second exhaust gas flow is tapped from a location upstream of an aft exit of the core engine.
15 . The aircraft propulsion system as recited in claim 11 , including a precooler where the first exhaust gas flow is cooled prior to communication with the desiccation system.
16 . The aircraft propulsion system as recited in claim 11 , wherein the evaporator system is in thermal communication with both the first exhaust gas flow and the second exhaust gas flow.