HYDROGEN STEAM INJECTED TURBINE ENGINE WITH TURBOEXPANDER HEAT RECOVERY
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United States of America Patent
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Issued Date -
Mar 27, 2025
app pub date -
Dec 10, 2024
filing date -
Dec 10, 2024
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status (Latency Note)
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Abstract
A propulsion system for an aircraft includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with a gaseous fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section. A fuel system supplies a fuel to the combustor through a fuel flow path, a first heat exchanger thermally communicates a first heat load into a cooling flow, a turboexpander where a heated cooling flow from the first heat exchanger is expanded to generate shaft power and cooled to provide a cooled cooling flow, and a second heat exchanger thermally communicates a second heat load to the cooled cooling flow that is communicated from the turboexpander, cooling flow from the second heat exchanger is communicated to the combustor section.
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