Axial flow angled condenser arrangement for an aircraft propulsion system
An aircraft propulsion system includes a plurality of condenser pairs where water is condensed from the exhaust gas flow received through a corresponding one of the plurality of exhaust ducts. Each of the condenser pairs are angled relative to each other and the corresponding one of the plurality of exhaust ducts and each condenser of the plurality of condenser pairs comprises an inward facing side and an outward facing side through which a cooling air flow is communicated for cooling the exhaust gas flow.
1 . An aircraft propulsion system comprising:
a core engine comprising a compressor, combustor, and turbine section, wherein an inlet airflow is compressed communicated to the combustor, mixed with fuel, and ignited to generate an exhaust gas flow that is expanded through the turbine section;
a propulsor driven about a propulsor axis by the core engine;
an exhaust duct assembly comprising a central portion turning an exhaust gas flow radially outward through a plurality of radial struts into a corresponding one of a plurality of splitters configured to turn the exhaust gas flow axially rearward;
a plurality of condenser pairs where water is condensed from the exhaust gas flow received through a corresponding one of the plurality splitters, wherein each of the condenser pairs are angled relative to each other and the corresponding one of the plurality of exhaust ducts and each condenser of the plurality of condenser pairs comprises an inward facing side and an outward facing side through which a cooling air flow is communicated for cooling the exhaust gas flow
a plurality of water separators where water from corresponding ones of the plurality of condenser pairs is separated from the exhaust gas flow;
a plurality of evaporators disposed within corresponding one of the plurality of splitters of the exhaust duct assembly; and
a plurality of superheaters disposed within the central portion of the exhaust duct assembly.
2 . The aircraft propulsion system as recited in claim 1 , further comprising a cooling air duct assembly where a portion of inlet airflow is communicated to each of the plurality of condenser pairs and an aft side of each of the plurality of condenser pairs is closed to force the cooling airflow through each of the plurality of condenser pairs.
3 . The aircraft propulsion system as recited in claim 2 , further comprising a bypass duct where a portion of the inlet airflow is bypassed around the plurality of condenser pairs and the core engine.
4 . The aircraft propulsion system as recited in claim 1 , wherein the turbine section of the core engine is engine forward of the combustor and the compressor section and an inlet duct assembly communicates a portion of the inlet airflow to an inlet that is disposed aft of the compressor section.
5 . The aircraft propulsion system as recited in claim 4 , further comprising a power turbine coupled to drive the propulsor, the power turbine disposed engine forward of the core engine.
6 . The aircraft propulsion system as recited in claim 5 , further comprising a nacelle assembly disposed about the propulsor and the core engine, wherein the plurality of condenser pairs is supported within the nacelle.
7 . The aircraft propulsion system as recited in claim 1 , comprising an intercooling system where a portion of water recovered from the exhaust gas flow is injected into the compressor for cooling a core flow.
8 . A water recovery system for an aircraft propulsion system comprising:
an exhaust duct assembly comprising a central portion turning an exhaust gas flow radially outward through a plurality of radial struts into a corresponding one of a plurality of splitters configured to turn the exhaust gas flow axially rearward;
a plurality of condenser pairs where water is condensed from an exhaust gas flow received through a corresponding one of a plurality of the splitters, wherein each of the condenser pairs are angled relative to each other and the corresponding one of the plurality of exhaust ducts and a cooling airflow is communicated through each condenser into a space between corresponding ones of the condenser pairs;
a plurality of water separators where water from corresponding ones of the plurality of condenser pairs is separated from the exhaust gas flow;
an evaporator where water from the plurality of water separators is transformed into a steam flow and communicated to a combustor, wherein the evaporator comprises a plurality of evaporators disposed within a corresponding one of the plurality of splitters; and
a plurality of superheaters where steam flow is further heated.
9 . The water recovery system as recited in claim 8 , wherein each condenser of the plurality of condenser pairs comprises an outward facing side in flow communication with a cooling air flow and an inward facing side through which the cooling airflow is exhausted.
10 . The water recovery system as recited in claim 9 , wherein the inward facing side of each of the plurality of condenser pairs face each other.
11 . The water recovery system as recited in claim 8 , further comprising a nacelle, wherein the plurality of condenser pairs and the plurality of water separators are supported in the nacelle and wherein the nacelle includes a cooling air duct where a portion of inlet airflow is communicated to each of the plurality of condenser pairs for providing a cooling flow through each of the plurality of condenser pairs.
12 . The water recovery system as recited in claim 11 , wherein the nacelle comprises a bypass duct where a portion of an inlet airflow is bypassed around the plurality of condenser pairs and a core engine.
13 . A method of operating an aircraft propulsion system comprising:
generating an exhaust gas flow with a core engine comprising a compressor, combustor, and turbine section;
coupling a propulsor to a power turbine configured to be driven by expansion of the exhaust gas flow about a propulsor axis by the core engine;
communicating the exhaust gas flow through an exhaust duct assembly comprising a central portion turning an exhaust gas flow radially outward through a plurality of radial struts into a corresponding one of a plurality of splitters configured to turn the exhaust gas flow axially rearward;
condensing water in a plurality of condensers pairs wherein each of the condenser pairs are angled relative to each other and a corresponding one of a plurality of splitters and each condenser of the plurality of condenser pairs comprises an outward facing side in flow communication with a cooling air flow and an inward facing side through which the cooling air flow is exhausted;
separating water from the exhaust gas flow in one of a plurality of water separators;
generating a steam flow from water extracted from the exhaust gas flow in an evaporator; and
heating the steam flow from the evaporator in a superheater disposed within a corresponding one of the plurality of exhaust ducts.