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US 8,783,044 B2Granted
Turbine stator nozzle cooling structure
AssigneeALSTOM Technology Ltd
InventorsUlrich Steiger, Jonas Hurter
Life of this patent
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AssigneeALSTOM Technology Ltd
InventorsUlrich Steiger, Jonas Hurter
Estimating the term…
In a gas turbine, a plurality of burners, which are arranged concentrically to the rotational axis in a regular arrangement, each directing hot gas through an associated combustion chamber outlet into a turbine, at the inlet of which a second plurality of stator blades are arranged in a ring, uniformly spaced apart around the rotational axis. Cooling openings are provided, which are distributed over the circumference, through which cooling air is injected into the hot gas flow at the combustion chamber outlet. An improvement of the flow conditions in the hot gas is achieved by the cooling openings being divided into first cooling opening groups and second cooling opening groups. The arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades, and in that the arrangement of the second cooling opening groups corresponds to the regular arrangement of the burners.
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,
A method for operating a gas turbine having a plurality of burners, arranged concentrically to a rotational axis in a regular arrangement, the burners having a corresponding combustion chamber outlet via which hot gas is injected into a turbine, a plurality of stator blades are operated and arranged in a ring, uniformly spaced apart around the rotational axis at an inlet of the turbine, said gas turbine comprises cooling openings, which operate, and are distributed over the circumference and through which cooling air is injected into the hot gas flow, the method comprising:
Dependencies are inferred from the claim text.