Patent ID: 9719684
Date: 2017-08-01
CPC Classifications: F23R,Y02T,Y10T

Claim:
1. A gas turbine engine combustor liner comprising: a hot side wall and a cold side wall configured for installation in a gas turbine engine to separate a combustion chamber from a cooling air source, the hot side wall and the cold side wall each comprising metal alloy sheet material; the hot side wall having a plurality of hot side holes projecting through its thickness for fluid communication with the combustion chamber; the cold side wall having a plurality of cold side holes projecting through its thickness for fluid communication with the cooling air source and including a plurality of pedestals that connect to the hot side wall such that a plurality of fluid flow passages are defined between the hot side wall and cold side wall and between the pedestals; the cold side holes being in fluid communication with the hot side holes via the fluid flow passages so as to create a cooling flow path from the cooling air source to the combustion chamber; and first and second arrangements of a plurality of the hot side holes, the cold side holes, and the fluid flow passages defining respective first and second porous regions in the combustor liner having respective first and second porosities; wherein at least one of 1) the plurality of hot side holes or 2) the plurality of cold side holes include holes of a first diameter and of a second diameter that is different from the first diameter; and wherein the first arrangement that defines the first porous region has the hot side holes of the first diameter, and the second arrangement that defines the second porous region has the hot side holes of the second diameter that is different than the first diameter.