COMBUSTOR WALL HAVING COOLING ELEMENT(S) WITHIN A COOLING CAVITY

摘要

A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a cooling element. The shell defined a first set of apertures. The heat shield defines a second set of apertures. The cooling element extends between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield. The tapered cavity is fluidly coupled with the first and the second sets of apertures. The cooling element is thermally coupled to one of the shell and the heat shield.