Patent ID: 8783044

Claim:
A gas turbine, comprising a plurality of burners, arranged concentrically to a rotational axis in a regular arrangement, each burner directing hot gas through an associated combustion chamber outlet into a turbine, a plurality of stator blades are arranged in a ring, at an inlet of the turbine, uniformly spaced apart around the rotational axis, the gas turbine comprises cooling openings which are distributed over the circumference and through which cooling air can be injected into the hot gas flow at the combustion chamber outlet, the cooling openings, with regard to the passage which is formed by the hot gas flow, are arranged in the region of an inner encompassing gap and are divided into first cooling opening groups and second cooling opening groups, wherein the periodicity of the first cooling opening groups is equal to the periodicity of the stator blades, and each of the first cooling opening groups has a same number of cooling openings, wherein the periodicity of the second cooling opening groups is equal to the periodicity of the burners, and wherein the cooling openings of the first cooling opening groups are unevenly distributed across the plurality of burners to reduce effects of a bow wave.