Patent ID: 6955053

Claim:
For a gas turbine engine that employs an annular combustor with radial fuel injection, a gas turbine annular combustor that has an annular outlet and a liner with liner surfaces comprising a dome, an outer wall, and an inner wall, comprising: angled effusion cooling holes in at least one of the liner surfaces that have a swirl angle from the surface in a direction that is generally tangential to the axial flow of combustion gas in the combustor toward the outlet to effectuate swirling of combustion gases in the combustor; wherein the outer wall and the inner wall have angled cooling holes and the angled cooling holes have both a swirl angle and a downstream angle from the surface in a direction generally parallel the axial flow of combustion gas in the combustor toward the outlet; and wherein the combustor has a dome with effusion cooling holes and associated cooling strips.