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RADIAL COOLING SYSTEM FOR GAS TURBINE ENGINE COMPRESSORS

  • US 20190211683A1
  • Filed: 01/08/2018
  • Published: 07/11/2019
  • Est. Priority Date: 01/08/2018
  • Status: Active Grant
First Claim
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1. A gas turbine engine, comprising:

  • a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades;

    a first bore cavity between the first rotor and the second rotor;

    a first fluid passageway configured to provide cooled air to the first bore cavity; and

    a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.

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