COMBUSTOR LINER FOR A CAN-ANNULAR GAS TURBINE ENGINE AND A METHOD FOR CONSTRUCTING SUCH A LINER

摘要

A combustor liner (30) for a can-annular gas turbine engine (10) and a method for constructing such a liner are provided. The combustor liner includes an annular wall member (32). A cooling channel (34, 42, 50, 54, 56, 58) is formed through the wall member and extends from an inlet end of the liner to an outlet end of the liner. A property of the cooling channel may be varied along a length of the cooling channel. The cooling channel may be formed through the combustor liner using an electro-chemical machining (ECM) process or a three dimensional printing process (3DP).