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Gas turbine engine configurations

  • US 8,669,670 B2
  • Filed: 09/06/2011
  • Issued: 03/11/2014
  • Est. Priority Date: 09/03/2010
  • Status: Active Grant
First Claim
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1. A gas turbine engine, comprising:

  • at least first and second turbo-compressor spools, each of the at least first and second turbo-compressor spools comprising a centrifugal compressor in mechanical communication with a radial turbine;

    at least one intercooler positioned in a fluid path between the at least first and second turbo-compressor spools;

    a recuperator operable to transfer thermal energy from an output gas of a power turbine to a compressed gas produced by the at least first and second turbo-compressor spools and thereby form a further heated gas; and

    a combustor operable to combust a fuel in the presence of the further heated gas;

    wherein;

    a first inlet gas to a first compressor in the first turbo-compressor spool enters the first compressor along a first axis;

    a first compressed gas from the first compressor exits the first compressor along a second axis;

    the first compressed gas to a second compressor in the second turbo-compressor spool enters the second compressor along a third axis;

    a second compressed gas from the second compressor exits the second compressor along a fourth axis; and

    wherein the second axis is rotatable about the first axis and fourth axis is rotatable about the third axis.

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