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GAS TURBINE ENGINE DRIVEN BY SCO2 CYCLE WITH ADVANCED HEAT REJECTION

  • US 20170058834A1
  • Filed: 06/09/2016
  • Published: 03/02/2017
  • Est. Priority Date: 06/15/2015
  • Status: Active Grant
First Claim
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1. A gas turbine engine, comprising:

  • a shaft comprising a first compressor, a fan assembly, and a power circuit that provides power to the shaft in a closed-loop system;

    an inner housing that houses;

    at least a portion of the shaft;

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

    a 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;

    a heat exchanger positioned in the second air passageway that rejects heat from the power circuit 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 the first volume; and

    as the heat rejection stream.

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