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GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION

  • US 20160090844A1
  • Filed: 04/15/2015
  • Published: 03/31/2016
  • Est. Priority Date: 04/23/2014
  • Status: Active Grant
First Claim
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1. A component for a gas turbine engine comprising:

  • an exterior surface providing pressure and suction sides, a cooling passage in the component includes a serpentine passageway having first and second passes respectively configured to provide fluid flow in opposite directions from one another, the first pass includes first and second portions nested relative to one another and overlapping in a thickness direction, the first and second portions adjacent to one another by sharing a common wall, the first portion provided on the suction side, and the second portion provided on the pressure side.

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