cycle with independent shafts for combustion cycle elements and propulsion elements
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United States of America Patent
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May 29, 2018
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N/A
app pub date -
Jun 17, 2016
filing date -
Jun 19, 2015
priority date (Note) -
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Abstract
A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.
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