Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor

摘要

A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.