Abstract: A combustor for a gas turbine engine is provided, and includes an inner case; an outer case circumscribing the inner case and forming an annular pressure vessel therebetween; an inner liner positioned within the annular pressure vessel; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner; and an igniter coupled to the outer case and extending to the outer liner such that the igniter is positioned to ignite an air and fuel mixture in the combustion chamber. The igniter includes a protrusion for coupling the igniter to the outer liner.

Abstract: A combustor for a turbine engine includes an outer liner and an inner liner circumscribed by the outer liner to form a combustion chamber therewith in which an air and fuel mixture is combusted to form streamlines of combustion gases. A first plurality of effusion cooling holes is formed in at least one of the inner or outer liners, with the first plurality of effusion cooling holes being oriented as a function of the streamlines.