Abstract: A combustor for gas turbine engine, wherein: a plurality of impingement-cooling holes are opened passing through an external wall of a liner for cooling air to blow out towards the outer surface of an internal wall of the liner; a plurality of pin-fins are formed on the outer surface of the internal wall of the liner; a plurality of effusion cooling holes are opened passing through the internal wall of the liner for cooling air to blow out along the inner surface of the internal wall of the liner. The top surface of each pin-fin is not in contact with the inner surface of the external wall of the liner and the ratio of the height of the pin-fin to the equivalent diameter of the impingement-cooling hole is set to be 1.0-3.0.

Abstract: In the invention, stator blades are arranged in such a manner that respective intervals between the adjacent stator blades (SV) become unequal at least partly. If the stator blades are arranged as mentioned above, there are formed wave fronts having different moving directions and phases, and these wave fronts are interfered with each other so as to be attenuated. Accordingly, an interference noise is reduced. Therefore, in accordance with the invention, it is possible to reduce an interference noise without enlarging a rotor stator blade interval as well as reducing a used amount of a sound absorption material.

Abstract: In the invention, stator blades are arranged in such a manner that respective intervals between the adjacent stator blades (SV) become unequal at least partly. If the stator blades are arranged as mentioned above, there are formed wave fronts having different moving directions and phases, and these wave fronts are interfered with each other so as to be attenuated. Accordingly, an interference noise is reduced. Therefore, in accordance with the invention, it is possible to reduce an interference noise without enlarging a rotor stator blade interval as well as reducing a used amount of a sound absorption material.