A COOLED WALL ASSEMBLY FOR A COMBUSTOR AND METHOD OF DESIGN

摘要

A wall assembly 60 that may be for a combustor of a gas turbine engine 20 includes a liner 74 having a hot face 104 that defines a combustion chamber 66, an opposite cold face 106, and a plurality of effusion holes 114. A shell 70 of the assembly 60 is spaced outward from the cold face 106 and includes a plurality of impingement holes 112 each having a centerline 118 orientated substantially normal to the cold face 106. A plurality of cooling member arrays 130 of the liner 74 each include a first plurality of members 132 that may be pins 132 projecting outward from the cold face 106 to conduct heat out of the liner 74. Each array 130 is spaced between adjacent effusion holes 114 and is symmetrically orientated about the respective centerline 118.