Gas turbine engine driven by sCO2 cycle with advanced heat rejection

  • US 10,443,544 B2
  • Filed: 06/09/2016
  • Issued: 10/15/2019
  • Est. Priority Date: 06/15/2015
  • Status: Active Grant
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First Claim
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1. A gas turbine engine, comprising:

  • a shaft having mounted thereto a first compressor, a second compressor, a turbine, and a fan assembly;

    a power circuit that provides power to the shaft in a closed-loop system that includes a working fluid heated by a combustor, the power circuit comprising the turbine and the second compressor;

    an inner housing that houses;

    at least a portion of the shaft;

    the second compressor;

    the turbine;

    the first compressor for compressing a core stream of air; and

    the combustor to heat the working fluid when it enters the combustor;

    a baffle that encloses a portion of the inner housing and forms a first air passageway therebetween;

    a nacelle that encloses a portion of the baffle and forms a second air passageway therebetween; and

    a heat exchanger positioned in the second air passageway that rejects heat from the working fluid into a heat rejection stream of air passing through the second air passageway;

    wherein air is accelerated as streams in parallel and via the fan assembly;

    as the core stream into the inner housing;

    as a bypass flow stream of air through a first volume; and

    as the heat rejection stream.

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