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Gas turbine engine airfoil cooling passage configuration

  • US 10,641,100 B2
  • Filed: 04/15/2015
  • Issued: 05/05/2020
  • Est. Priority Date: 04/23/2014
  • Status: Active Grant
First Claim
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1. A component for a gas turbine engine comprising:

  • pressure and suction walls that together provide an exterior surface and respectively provide 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 portion extends to both of and is at least partially defined by the pressure and suction walls, the second portion extends to both of and is at least partially defined by the pressure and suction walls, the first and second portions adjacent to one another by sharing a common wall that extends to both of the pressure and suction walls, the first portion provided more substantially on the suction side than the pressure side, and the second portion provided more substantially on the pressure side than the suction side.

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