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Gas turbine engine heat exchanger fins with periodic gaps

  • US 9,051,943 B2
  • Filed: 11/04/2010
  • Issued: 06/09/2015
  • Est. Priority Date: 11/04/2010
  • Status: Active Grant
First Claim
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1. A gas turbine engine comprising:

  • a core supported relative to a fan case by the core including a core nacelle, and a fan duct provided between the core nacelle and the fan case, wherein the core includes a compressor section and a bleed cavity is provided within the core and in fluid communication with the compressor section;

    an actuation system component arranged within the bleed cavity, the actuation system component configured to actuate variable stator vanes in the compressor section; and

    a heat exchanger including first and second sides opposite one another, the second side including a set of rows of fins exposed to the bleed cavity, the set of fins having gaps between discrete fins in a given row.

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