| CPC F02C 3/30 (2013.01) [F02C 7/141 (2013.01); F02C 7/16 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01); F05D 2270/08 (2013.01)] | 18 Claims |
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1. A method of operating an aircraft propulsion system, the aircraft propulsion system 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 split into a first exhaust gas flow and a second exhaust gas flow, a condenser where water from the second exhaust gas flow is condensed and extracted, wherein the first exhaust gas flow bypasses the condenser, an evaporator system where thermal energy from at least the second 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, an exhaust compressor which receives the second exhaust gas flow from the condenser and compresses the second exhaust gas flow to form a higher pressure exit flow, and an exhaust mixer downstream from the condenser, wherein the first exhaust gas flow and the higher pressure exit flow are merged within the exhaust mixer, the method comprising:
generating the exhaust flow containing a mixture of steam, compressed air, and fuel;
splitting the generated exhaust flow into the first exhaust flow and the second exhaust flow with the second exhaust flow being less than half of the generated exhaust flow;
thermally communicating the second exhaust flow with a cold sink in the condenser for cooling the second exhaust flow;
condensing and extracting water from the cooled second exhaust flow; and
controlling the second exhaust flow through the condenser by selectively operating the exhaust compressor based on a cooling capacity of the cold sink.
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4. 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 split into a first exhaust gas flow and a second exhaust gas flow;
a condenser where water from the second exhaust gas flow is condensed and extracted, wherein the first exhaust gas flow bypasses the condenser;
an evaporator system where thermal energy from at least the second 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; and
an exhaust compressor which receives the second exhaust gas flow from the condenser and compresses the second exhaust gas flow to form a higher pressure exit flow; and
an exhaust mixer downstream from the condenser, wherein the first exhaust gas flow and the high pressure exit flow are merged within the exhaust mixer.
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